WO2018076468A1 - 屏蔽装置及无人飞行器 - Google Patents

屏蔽装置及无人飞行器 Download PDF

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Publication number
WO2018076468A1
WO2018076468A1 PCT/CN2016/108994 CN2016108994W WO2018076468A1 WO 2018076468 A1 WO2018076468 A1 WO 2018076468A1 CN 2016108994 W CN2016108994 W CN 2016108994W WO 2018076468 A1 WO2018076468 A1 WO 2018076468A1
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WO
WIPO (PCT)
Prior art keywords
casing
mounting portion
unmanned aerial
aerial vehicle
shielding device
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2016/108994
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English (en)
French (fr)
Inventor
冯建刚
唐尹
王登
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
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Filing date
Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201680087991.9A priority Critical patent/CN109644581B/zh
Publication of WO2018076468A1 publication Critical patent/WO2018076468A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • 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
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields

Definitions

  • the present invention relates to aircraft technology, and more particularly to a shielding device and an unmanned aerial vehicle.
  • Unmanned aerial vehicles because of their flexibility, rapid response, unmanned flight, low operational requirements, etc., are widely used in military, scientific research and civil affairs to carry out transportation, delivery, surveillance, and application in various fields. Scouting, exploration, shooting and other tasks.
  • the unmanned aerial vehicle is positioned and navigated by a Global Positioning System (GPS) module.
  • GPS Global Positioning System
  • the GPS module is easily interfered by other electronic components such as batteries in the unmanned aerial vehicle, and affects the GPS.
  • the working performance of the module leads to inaccurate positioning and navigation, even failure.
  • the present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention needs to provide a shielding device and an unmanned aerial vehicle.
  • a shielding device for an unmanned aerial vehicle comprising a global positioning system module, the shielding device comprising:
  • the cover portion housing the global positioning system module
  • the mounting portion extends from the cover portion and surrounds the cover portion, and the cover portion and the mounting portion are made of a metal material and integrally formed.
  • the cover is spaced from the global positioning system module.
  • the cover portion is provided with a through hole.
  • the mounting portion is provided with a plurality of engaging holes.
  • the mounting portion is formed with a plurality of protrusions, each of which is provided with a receiving groove.
  • An unmanned aerial vehicle comprising a first casing fixed to the first casing a global positioning system module and a shielding device, the shielding device comprising:
  • the cover portion housing the global positioning system module
  • a mounting portion extending from the covering portion and surrounding the covering portion, the mounting portion being mounted on the first casing, the covering portion and the mounting portion being made of a metal material, And integrated.
  • the cover is spaced from the global positioning system module.
  • the cover portion is provided with a through hole
  • the UAV further includes a battery module and a wire, the wire passing through the through hole and connecting the global positioning system module and the Battery module.
  • the UAV further includes a filler for filling a gap formed by the wire through the through hole.
  • the shape of the mounting portion matches the shape of the first housing to conform to the first housing.
  • the mounting portion is secured to the first housing by one or more of adhesive bonding, threading, snapping, welding.
  • the mounting portion is provided with a plurality of engaging holes
  • the first housing includes a plurality of latching blocks
  • the mounting portion passes through the plurality of engaging holes and the plurality of latching blocks A snap is fixed to the first casing.
  • the casing includes a plurality of ribs, and the mounting portion is formed with a plurality of protrusions, each of the protrusions is provided with a receiving groove, and each of the receiving slots is for receiving one of the Ribs.
  • the shielding device and the unmanned aerial vehicle of the embodiments of the present invention can effectively shield the interference of the electronic components in the UAV on the global positioning system module, so as to ensure that the global positioning system module can accurately during the flight of the unmanned aerial vehicle. Positioning and navigation.
  • FIG. 1 is a schematic perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 2 is a perspective exploded view of the unmanned aerial vehicle of FIG. 1.
  • FIG. 3 is a perspective exploded view showing a partial structure of another view of the UAV of FIG. 2.
  • FIG. 4 is a perspective view of the shielding device of the unmanned aerial vehicle of FIG. 3.
  • first and second are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
  • features defining “first” or “second” may include one or more of the described features either explicitly or implicitly.
  • the meaning of "a plurality” is two or more unless specifically and specifically defined otherwise.
  • connection In the description of the present invention, it should be noted that the terms “installation”, “connected”, and “connected” are to be understood broadly, and may be fixed or detachable, for example, unless otherwise explicitly defined and defined. Connected, or connected in one piece; may be mechanically connected, or may be electrically connected or may communicate with each other; may be directly connected, or may be indirectly connected through an intermediate medium, and may be internal to the two elements. Or the interaction of two components.
  • the specific meanings of the above terms in the present invention can be understood on a case-by-case basis.
  • the first feature "on” or “under” the second feature may include direct contact of the first and second features, and may also include first and second features, unless otherwise specifically defined and defined. It is not in direct contact but through additional features between them.
  • the first feature "above”, “above” and “above” the second feature includes the first feature directly above and above the second feature, or merely indicating that the first feature level is higher than the second feature.
  • the first feature “below”, “below” and “below” the second feature includes the first feature directly below and below the second feature, or merely the first feature level being less than the second feature.
  • the unmanned aerial vehicle 100 provided by the embodiment of the present invention is a quadrotor aircraft, that is, an aircraft having four rotor assemblies. It can be understood that the UAV 100 can also be a six-rotor aircraft, an eight-rotor aircraft, a twelve-rotor aircraft, etc., and even the unmanned aerial vehicle 100 can be a single-rotor aircraft; in addition, in some embodiments, the unmanned aerial vehicle 100 can For fixed-wing aircraft, or fixed-wing-rotor hybrid aircraft.
  • the rotor assembly 16 includes a motor (not shown) and a propeller (not shown) coupled to a motor (not shown).
  • the propeller of the rotor assembly 16 is not shown, but does not represent a rotor.
  • the assembly 16 can dispense with the propeller.
  • a motor (not shown) can drive the propeller to rotate to provide power to fly the UAV 100.
  • the UAV 100 includes a first casing 10, a second casing 20 connected to the first casing 10, a battery module 30, a Global Positioning System (GPS) module 40, and a shielding device. 50.
  • the first casing 10 and the second casing 20 are combined to form a receiving space 10a, and the battery module 30, the GPS module 40, and the shielding device 50 are housed in the accommodating space 10a.
  • GPS Global Positioning System
  • the first cabinet 10 includes a first body portion 12 and a first arm portion 14.
  • First body portion 12 inward
  • the bottom surface of the recess is provided with a plurality of ribs 122 and a plurality of latches 124.
  • the plurality of ribs 122 are uniformly distributed radially around the center of the first body portion 12.
  • the number of first arms 14 corresponds to the number of rotor assemblies 16 of the UAV 100 for cooperating with the second housing 20 to position the corresponding rotor assembly 16 at a predetermined position.
  • the first arm portion 14 extends radially from the first body portion 12, and more specifically, the first arm portion 14 is symmetrically disposed about the center of the first body portion 12.
  • the second cabinet 20 includes a second body portion 22, a second arm portion 24, and a joint portion 26.
  • the second body portion 22 is recessed inward.
  • the number of second arm portions 24 corresponds to the number of rotor assemblies 16 of the UAV 100 and the number of first arm portions 14 for mating with the first arm portion 14 to set the corresponding rotor assembly 16 at a predetermined position.
  • the second arm portion 24 extends radially from the second body portion 22, and more specifically, the second arm portion 24 is symmetrically disposed about the center of the second body portion 22.
  • Each of the joint portions 26 extends from each of the first arm portions 14 in a direction away from the receiving space 10a for engagement with a stand (not shown) of the UAV 100 to enable the UAV to stand on the ground.
  • the second casing 20 may be combined with the first casing 10 by any one or more of gluing, screwing, engaging, welding, etc., and the recess of the first body portion 12 and the first body portion 22 The recesses collectively form the receiving space 10a.
  • the battery module 30 is further integrated with a sensor (not shown) and a processing chip (not shown) for implementing functions such as obstacle avoidance, positioning, speed measurement, navigation, and the like.
  • the GPS module 40 and the shielding device 50 are fixed on the first casing 10.
  • the GPS module 40 and the battery module 30 are respectively disposed on both sides of the shielding device 50 and electrically connected by wires (not shown), and the shielding device 50 is
  • the GPS module 40 is housed.
  • the shielding device 50 includes a covering portion 52 and a mounting portion 54 extending from the covering portion 52 and surrounding the covering portion 52.
  • the cover portion 52 is a cover structure, and includes a cover end 521, a receiving end 524 opposite to the cover end, and a side wall 526 connecting the cover end and the receiving end.
  • the shape of the cover structure may be a circle, a triangle, an ellipse, a rectangle, or other regular or irregular shapes. In the embodiment, the cover structure has a circular shape.
  • the cover end 521 defines a through hole 522 for electrically connecting the wires of the GPS module 40 and the battery module 30.
  • the receiving end 524 is provided with a receiving slot 523 for receiving the GPS module 40.
  • the mounting portion 54 extends from the side wall 526 of the cover portion 52 to surround the cover portion 52.
  • the mounting portion 54 is formed with a plurality of engaging holes 542 corresponding to the plurality of blocks 124 and a plurality of protrusions corresponding to the plurality of ribs 122. 544, each of the protrusions 544 defines a receiving slot 545, and each receiving slot 545 is configured to receive a rib 122.
  • the mounting portion 54 is fixed to the first casing 10 by the plurality of engaging blocks 124 being engaged with the corresponding plurality of engaging holes 542. At this time, the plurality of ribs 122 are housed in the corresponding plurality of receiving grooves 545.
  • the shape of the mounting portion 54 matches the shape of the first housing 10 to fit the first housing 10.
  • the shape of the mounting portion 54 matches the shape of the first housing 10 to be completely attached to the first housing 10. In other words, there is no gap between the mounting portion 54 and the first casing 10.
  • the GPS module 40 is housed in the receiving groove and spaced apart from the covering portion 52, that is, there is a gap therebetween.
  • the UAV 100 of the present invention uses the cover portion 52 of the shielding device 50 to receive the GPS module 40, so that the GPS module 40 is isolated from other electronic components such as the battery module 30, and effectively shields other electronic components from the GPS module.
  • the interference of 40 avoids affecting the working performance of the GPS module and ensures accurate positioning and navigation.
  • the unmanned aerial vehicle 100 is locked and fixed on the first casing 10 by the mounting portion 54 to fit the shielding device 50 and the first casing 10, so that the shielding device 50 can be easily installed and disassembled, and the operation is simple.
  • the first casing 10 the second casing 20 and the internal components generate vibration, and the spacing between the covering portion 52 and the GPS module 40 can provide a moving space.
  • the shielding device 50 When installed, the shielding device 50 can be prevented from colliding with the GPS module 40 and damaging the GPS module 40, ensuring the positioning and navigation accuracy of the UAV 100, and prolonging the service life of the GPS module 40; on the other hand, the covering portion
  • the movement space provided by the gap between the 52 and the GPS module 40 effectively prevents the vibration generated by the shielding device 50 from directly acting on the GPS module 40, which may cause the GPS module 40 to loose or fall off, thereby affecting the positioning of the UAV 100,
  • the accuracy of the navigation likewise, the movement space provided by the gap between the cover 52 and the GPS module 40 can effectively prevent the vibration generated by the GPS module 40 from directly acting on the shielding device 50, which may cause the shielding device 50 to loose or Falling off, thereby reducing the shielding effectiveness, will also affect the positioning and navigation accuracy of the UAV 100.
  • the shielding device 50 can effectively shield the electromagnetic interference generated by other electronic components to ensure the GPS mode.
  • the working performance of the group 40; on the other hand, the fitting design of the mounting portion 54 and the first casing 10 can save internal space and facilitate the layout between the components.
  • the ribs 122 in the first casing 10 can be used to strengthen the structure of the first casing 10, and the mounting portion 54 forms a projection 544 for receiving the ribs 122, so that the mounting portion 54 and the first casing can be ensured. 10 good fit.
  • the ribs 122 on the first casing 10 may be omitted, correspondingly, the mounting portion
  • the protrusions on the 54 can also be omitted, that is, the structure of the first casing 10 and the mounting portion 54 can be arbitrarily set, and only the shape of the mounting portion 54 needs to be matched with the shape of the first casing 10 to match the first casing 10 . Fit it.
  • the distance between the cover portion 52 and the GPS module 40 can be appropriately set according to the specific size of the components in the first casing 10.
  • the cover portion 52 can also be spaced from the GPS module 40. For example, just touch/complete fit.
  • the cover portion 52 is integrally formed with the mounting portion 54.
  • a metal plate of a suitable size can be selected for stamping and formed, and matched with the specific structure of the first casing 10 to complete the assembly.
  • the UAV 100 further includes a filler for filling a gap formed by the wire through the through hole 522.
  • the filler may be made of metal, for example, the filler may be made of any one or more of very thin gold, silver, copper, copper, iron, aluminum.
  • the diameter of the wire is smaller than the diameter of the through hole 522. After the wire passes through, a gap is formed between the through hole 522 and the wire, and the gap will affect the shielding effect of the shielding device 50 on electromagnetic interference, and the filler will be fixed. To a lesser extent, the effect on the shielding effect after opening the through hole 522 is reduced.
  • the mounting portion 54 can also be secured to the first housing 10 by any one or more of adhesive bonding, threading, welding, and the like.
  • the threaded connection also facilitates the installation and removal of the shielding device 50.
  • the adhesive bonding or welding method does not need to open other structures, and can be directly fixed to the first casing 10, and the process is simple and easy to operate.
  • the shielding device 50 is made of a metallic material.
  • the shielding device 50 is made of any one or more of gold, silver, copper, copper, iron, aluminum.
  • the shielding device 50 made of a metal material can have a good shielding effect against electromagnetic interference, and secondly, the metal has a certain rigidity after molding, is not easily deformed, and is beautiful and practical.
  • the shielding device 50 has a thickness of greater than or equal to 0.2 millimeters.
  • the shielding device 50 has good shielding performance without occupying excessive internal space of the first casing 10.
  • first and second are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
  • features defining “first” or “second” may include at least one of the features, either explicitly or implicitly.
  • the meaning of "a plurality” is at least two, such as two, three, etc., unless specifically defined otherwise.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

一种屏蔽装置（50）及无人飞行器（100），其中屏蔽装置（50）用于无人飞行器（100）。无人飞行器（100）包括全球定位系统模组（40），屏蔽装置（50）包括遮盖部（52）及安装部（54），遮盖部（52）收容全球定位系统模组（40），安装部（54）自遮盖部（52）延伸并环绕遮盖部（52）。所述屏蔽装置（50）及无人飞行器（100），可以有效地屏蔽无人飞行器（100）中电子元器件对全球定位系统模组（40）的干扰，以保证全球定位系统模组（40）在无人飞行器（100）的飞行过程中能够准确的定位与导航。

Description

屏蔽装置及无人飞行器 技术领域
本发明涉及飞行器技术，特别涉及一种屏蔽装置及无人飞行器。
背景技术
无人飞行器，因具有机动灵活、反应快速、无人飞行、操作要求低等优点，而被广泛地应用于军事、科研以及民事三大领域，以执行各领域应用中的运输、投递、监视、侦查、勘探、拍摄等任务。无人飞行器通过全球定位系统(Global Positioning System,GPS)模组进行定位与导航，在定位与导航过程中，GPS模组容易受到无人飞行器中诸如电池等其他电子元器件的干扰，而影响GPS模组的工作性能，导致定位与导航不准，甚至失败。
发明内容
本发明旨在至少解决现有技术中存在的技术问题之一。为此，本发明需要提供一种屏蔽装置及无人飞行器。
一种屏蔽装置，用于无人飞行器，所述无人飞行器包括全球定位系统模组，所述屏蔽装置包括：
遮盖部，所述遮盖部收容所述全球定位系统模组；及
安装部，所述安装部自所述遮盖部延伸并环绕所述遮盖部，所述遮盖部及所述安装部由金属材料制成，且一体成型。
在某些实施方式中，所述遮盖部与所述全球定位系统模组间隔。
在某些实施方式中，所述遮盖部开设有通孔。
在某些实施方式中，所述安装部开设有多个卡合孔。
在某些实施方式中，所述安装部形成有多个凸起，每个凸起开设有一个收容槽。
一种无人飞行器，所述无人飞行器包括第一机壳、固定在所述第一机壳上 的全球定位系统模组及屏蔽装置，所述屏蔽装置包括：
遮盖部，所述遮盖部收容所述全球定位系统模组；及
安装部，所述安装部自所述遮盖部延伸并环绕所述遮盖部，所述安装部装设在所述第一机壳上，所述遮盖部及所述安装部由金属材料制成，且一体成型。
在某些实施方式中，所述遮盖部与所述全球定位系统模组间隔。
在某些实施方式中，所述遮盖部开设有通孔，所述无人飞行器还包括电池模组及导线，所述导线穿过所述通孔并连接所述全球定位系统模组及所述电池模组。
在某些实施方式中，所述无人飞行器还包括填充物，所述填充物用于填充所述导线穿过所述通孔形成的间隙。
在某些实施方式中，所述安装部的形状与所述第一机壳的形状匹配以与所述第一机壳贴合。
在某些实施方式中，所述安装部通过粘胶粘合、螺纹连接、卡合、焊接中的一种或多种固定在所述第一机壳上。
在某些实施方式中，所述安装部开设有多个卡合孔，所述第一机壳包括多个卡块，所述安装部通过所述多个卡合孔与所述多个卡块卡合固定在所述第一机壳上。
在某些实施方式中，所述机壳包括多个凸肋，所述安装部形成有多个凸起，每个凸起开设有一个收容槽，每个所述收容槽用于收容一个所述凸肋。
本发明实施方式的屏蔽装置及无人飞行器，可以有效地屏蔽无人飞行器中电子元器件对全球定位系统模组的干扰，以保证全球定位系统模组在无人飞行器的飞行过程中能够准确的定位与导航。
本发明的附加方面和优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本发明的实践了解到。
附图说明
本发明的上述和/或附加的方面和优点从结合下面附图对实施方式的描述中将变得明显和容易理解，其中：
图1是本发明实施方式的无人飞行器的立体组装示意图。
图2是图1中的无人飞行器的立体分解示意图。
图3是图2中的无人飞行器的另一视角的部分结构的立体分解示意图。
图4是图3中的无人飞行器的屏蔽装置的立体示意图。
主要元件符号说明：
无人飞行器100、第一机壳10、收容空间10a、第一主体部12、凸肋122、卡块124、第一支臂部14、旋翼组件16、第二机壳20、第二主体部22、第二支臂部24、结合部26、电池模组30、全球定位系统模组40、屏蔽装置50、遮盖部52、罩设端521、通孔522、容置槽523、收容端524、侧壁526、安装部54、卡合孔542、凸起544、收容槽545。
具体实施方式
下面详细描述本发明的实施方式，所述实施方式的示例在附图中示出，其中自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。下面通过参考附图描述的实施方式是示例性的，仅用于解释本发明，而不能理解为对本发明的限制。
在本发明的描述中，需要理解的是，术语“中心”、“纵向”、“横向”、“长度”、“宽度”、“厚度”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”、“顺时针”、“逆时针”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括一个或者更多个所述特征。在本发明的描述中，“多个”的含义是两个或两个以上，除非另有明确具体的限定。
在本发明的描述中，需要说明的是，除非另有明确的规定和限定，术语“安装”、“相连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接；可以是机械连接，也可以是电连接或可以相互通讯；可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通 或两个元件的相互作用关系。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本发明中的具体含义。
在本发明中，除非另有明确的规定和限定，第一特征在第二特征之“上”或之“下”可以包括第一和第二特征直接接触，也可以包括第一和第二特征不是直接接触而是通过它们之间的另外的特征接触。而且，第一特征在第二特征“之上”、“上方”和“上面”包括第一特征在第二特征正上方和斜上方，或仅仅表示第一特征水平高度高于第二特征。第一特征在第二特征“之下”、“下方”和“下面”包括第一特征在第二特征正下方和斜下方，或仅仅表示第一特征水平高度小于第二特征。
下文的公开提供了许多不同的实施方式或例子用来实现本发明的不同结构。为了简化本发明的公开，下文中对特定例子的部件和设置进行描述。当然，它们仅仅为示例，并且目的不在于限制本发明。此外，本发明可以在不同例子中重复参考数字和/或参考字母，这种重复是为了简化和清楚的目的，其本身不指示所讨论各种实施方式和/或设置之间的关系。此外，本发明提供了的各种特定的工艺和材料的例子，但是本领域普通技术人员可以意识到其他工艺的应用和/或其他材料的使用。
请一并参阅图1至图3，本发明实施方式提供的无人飞行器100为四旋翼飞行器，即具有四个旋翼组件的飞行器。可以理解，无人飞行器100也可以为六旋翼飞行器、八旋翼飞行器、十二旋翼飞行器等，甚至，无人飞行器100可以为单旋翼飞行器；另外，在某些实施方式中，无人飞行器100可以为固定翼飞行器，或者固定翼-旋翼混合的飞行器。旋翼组件16包括电机(图未示)以及与电机(图未示)相连的螺旋桨(图未示)，在图示的实施方式中，旋翼组件16的螺旋桨并未示出，但并不表示旋翼组件16可以省去螺旋桨。电机(图未示)能够驱动螺旋桨转动，以提供无人飞行器100飞行的动力。
无人飞行器100包括第一机壳10、和与所述第一机壳10连接的第二机壳20、电池模组30、全球定位系统(Global Positioning System，GPS)模组40、以及屏蔽装置50。第一机壳10与第二机壳20结合形成收容空间10a，电池模组30、GPS模组40以及屏蔽装置50收容在收容空间10a内。
第一机壳10包括第一主体部12以及第一支臂部14。第一主体部12向内 凹陷，且凹陷的底面设置有多个凸肋122及多个卡块124，多个凸肋122围绕第一主体部12的中心呈均匀的放射状分布。第一支臂部14的数量对应于无人飞行器100的旋翼组件16的数量，用于与第二机壳20配合将对应的旋翼组件16设置在预定位置。本实施方式中，第一支臂部14自第一主体部12呈放射状延伸，更具体地，第一支臂部14关于第一主体部12的中心对称设置。
第二机壳20包括第二主体部22、第二支臂部24以及结合部26。第二主体部22向内凹陷。第二支臂部24的数量对应于无人飞行器100的旋翼组件16的数量以及第一支臂部14的数量，用于与第一支臂部14配合而将对应的旋翼组件16设置在预定位置。本实施方式中，第二支臂部24自第二主体部22呈放射状延伸，更具体地，第二支臂部24关于第二主体部22的中心对称设置。每个结合部26自每个第一支臂部14朝远离收容空间10a的方向延伸用于与无人飞行器100的脚架(图未示)结合而使得无人飞行器能够站立在地面上。第二机壳20可通过胶合、螺纹结合、卡合、焊接等方式中的任意一种或多种与第一机壳10结合在一起，而第一主体部12的凹陷和第一主体部22的凹陷共同形成收容空间10a。
电池模组30除了为无人飞行器100提供电力，电池模组30上还集成有用于实现避障、定位、测速、导航等功能的传感器(图未示)及处理芯片(图未示)。
GPS模组40及屏蔽装置50固定在第一机壳10上，GPS模组40与电池模组30分别设置在屏蔽装置50的两侧并通过导线(图未示)电连接，且屏蔽装置50收容GPS模组40。
请一并参阅图2至图4，屏蔽装置50包括遮盖部52及自遮盖部52延伸并环绕遮盖部52的安装部54。遮盖部52为罩体结构，包括罩设端521、与罩设端相背的收容端524及连接罩设端与收容端的侧壁526。罩体结构的形状可呈圆形、三角形、椭圆形、长方形、其他规则或不规则的形状，本实施方式中，罩体结构呈圆形。罩设端521开设有通孔522以供电连接GPS模组40与电池模组30的导线穿过。收容端524开设有容置槽523以用于收容GPS模组40。安装部54自遮盖部52的侧壁526延伸以环绕遮盖部52，安装部54形成有与多个卡块124对应的多个卡合孔542及与与多个凸肋122对应的多个凸起544，每个凸起544开设有一个收容槽545，每个收容槽545用于收容一个凸肋122。 安装部54通过多个卡块124卡合在对应的多个卡合孔542中而固定在第一机壳10上，此时，多个凸肋122收容在对应的多个收容槽545内。安装部54的形状与第一机壳10的形状匹配以与第一机壳10贴合，优选地，安装部54的形状与第一机壳10的形状匹配以与第一机壳10完全贴合，换言之，安装部54与第一机壳10之间没有缝隙。
屏蔽装置50安装在第一机壳10上时，GPS模组40收容在收容槽内并与遮盖部52间隔，即二者之间有间隙。
本发明提供的无人飞行器100利用屏蔽装置50的遮盖部52将GPS模组40收容，使得GPS模组40与电池模组30等其他电子元器件隔离，有效屏蔽其他电子元器件对GPS模组40的干扰，避免影响GPS模组的工作性能，保证定位与导航准确。另外，无人飞行器100通过安装部54卡合固定在第一机壳10上而将屏蔽装置50与第一机壳10配合安装，使得屏蔽装置50的安装及拆卸方便，操作简单。而且，在无人飞行器100起落过程中，第一机壳10、第二机壳20及内部的元件会产生振动，遮盖部52与GPS模组40的间隔可以提供一个移动空间，一方面在拆装时，可以避免屏蔽装置50碰撞到GPS模组40而损坏GPS模组40，保证无人飞行器100的定位、导航的准确度，也延长了GPS模组40使用寿命；另一方面，遮盖部52与GPS模组40的间隔所提供的移动空间有效避免屏蔽装置50产生的振动直接作用在GPS模组40上而可能导致GPS模组40的松动或脱落,从而影响无人飞行器100的定位、导航的准确度；同样地，遮盖部52与GPS模组40的间隔所提供的移动空间还可以有效避免GPS模组40产生的振动直接作用在屏蔽装置50上而可能导致屏蔽装置50的松动或脱落，从而降低屏蔽功效，同样也会影响无人飞行器100的定位、导航的准确度。再者，由于安装部54固定在第一机壳10上并与第一机壳10完全贴合，一方面，可以使得屏蔽装置50对其他电子元器件产生的电磁干扰形成有效屏蔽而保证GPS模组40的工作性能；另一方面，安装部54与第一机壳10的贴合设计可以节省内部空间便于元件之间的布设。第一机壳10内的凸肋122可用于对第一机壳10的结构起到加强作用，安装部54形成凸起544用于收容凸肋122，如此可保证安装部54与第一机壳10良好贴合。
在某些实施方式中，第一机壳10上的凸肋122可以省略，对应地，安装部 54上的凸起也可以省略，即，第一机壳10与安装部54的结构可以任意设置，只需要满足安装部54的形状与第一机壳10的形状匹配以与第一机壳10贴合即可。
在某些实施方式中，遮盖部52与GPS模组40的间隔距离可以根据第一机壳10内元件具体尺寸合理设置，例如，遮盖部52也可与GPS模组40之间不存在间隔，比如刚好接触/完全贴合。
在某些实施方式中，遮盖部52与安装部54一体成型。
如此，可简化屏蔽装置50的制造工艺，节省成本，例如，可选取大小合适的金属板冲压成型，并与第一机壳10具体结构相配合，完成装配。
在某些实施方式中，无人飞行器100还包括填充物，填充物用于填充导线穿过通孔522形成的间隙。填充物可由金属制成，例如，填充物可由很薄的金、银、铜、洋白铜、铁、铝中的任意一种或多种制成。
可以理解，导线的直径小于通孔522的直径，导线穿过后在通孔522与导线之间会形成间隙，而间隙将会影响屏蔽装置50对电磁干扰的屏蔽效果，而填充物将可以在一定程度上降低开设通孔522后对屏蔽效果的影响。
在某些实施方式中，安装部54还可通过粘胶粘合、螺纹连接、焊接等方式中的任意一种或多种相结合而固定在第一机壳10上。螺纹连接也易于屏蔽装置50的安装及拆卸。而粘胶粘合或焊接方式固定无需开设其他结构，可直接与第一机壳10固定，工艺简便，易于操作。
在某些实施方式中，屏蔽装置50由金属材料制成。
较佳地，在一些实施方式中，屏蔽装置50由金、银、铜、洋白铜、铁、铝中的任意一种或多种制成。
如此，一来采用金属材料制成的屏蔽装置50可以对电磁干扰起到良好的屏蔽效果，二来金属成型后具有一定的刚性，不易发生变形，美观实用。
在某些实施方式中，屏蔽装置50的厚度大于等于0.2毫米。
如此，屏蔽装置50在不占据第一机壳10过多内部空间的同时具有良好的屏蔽性能。
在本说明书的描述中，参考术语“一个实施方式”、“一些实施方式”、“示意性实施方式”、“示例”、“具体示例”、或“一些示例”等的描述意指结合所述 实施方式或示例描述的具体特征、结构、材料或者特点包含于本发明的至少一个实施方式或示例中。在本说明书中，对上述术语的示意性表述不一定指的是相同的实施方式或示例。而且，描述的具体特征、结构、材料或者特点可以在任何的一个或多个实施方式或示例中以合适的方式结合。
此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括至少一个该特征。在本发明的描述中，“多个”的含义是至少两个，例如两个，三个等，除非另有明确具体的限定。
尽管上面已经示出和描述了本发明的实施方式，可以理解的是，上述实施方式是示例性的，不能理解为对本发明的限制，本领域的普通技术人员在本发明的范围内可以对上述实施方式进行变化、修改、替换和变型。

Claims (13)

  1. 一种屏蔽装置，用于无人飞行器，所述无人飞行器包括全球定位系统模组，其特征在于，所述屏蔽装置包括：
    遮盖部，所述遮盖部收容所述全球定位系统模组；及
    安装部，所述安装部自所述遮盖部延伸并环绕所述遮盖部，所述遮盖部及所述安装部由金属材料制成，且一体成型。
  2. 如权利要求1所述的屏蔽装置，其特征在于，所述遮盖部与所述全球定位系统模组间隔。
  3. 如权利要求1所述的屏蔽装置，其特征在于，所述遮盖部开设有通孔。
  4. 如权利要求1所述的屏蔽装置，其特征在于，所述安装部开设有多个卡合孔。
  5. 如权利要求1所述的屏蔽装置，其特征在于，所述安装部形成有多个凸起，每个凸起开设有一个收容槽。
  6. 一种无人飞行器，其特征在于，所述无人飞行器包括第一机壳、固定在所述第一机壳上的全球定位系统模组及屏蔽装置，所述屏蔽装置包括：
    遮盖部，所述遮盖部收容所述全球定位系统模组；及
    安装部，所述安装部自所述遮盖部延伸并环绕所述遮盖部，所述安装部装设在所述第一机壳上，所述遮盖部及所述安装部由金属材料制成，且一体成型。
  7. 如权利要求6所述的无人飞行器，其特征在于，所述遮盖部与所述全球定位系统模组间隔。
  8. 如权利要求6所述的无人飞行器，其特征在于，所述遮盖部开设有通孔，所述无人飞行器还包括电池模组及导线，所述导线穿过所述通孔并连接所述全球定位系统模组及所述电池模组。
  9. 如权利要求8所述的无人飞行器，其特征在于，所述无人飞行器还包括填充物，所述填充物用于填充所述导线穿过所述通孔形成的间隙。
  10. 如权利要求6所述的无人飞行器，其特征在于，所述安装部的形状与所述第一机壳的形状匹配以与所述第一机壳贴合。
  11. 如权利要求10所述的无人飞行器，其特征在于，所述安装部通过粘胶 粘合、螺纹连接、卡合、焊接中的一种或多种固定在所述第一机壳上。
  12. 如权利要求10所述的无人飞行器，其特征在于，所述安装部开设有多个卡合孔，所述第一机壳包括多个卡块，所述安装部通过所述多个卡合孔与所述多个卡块卡合固定在所述第一机壳上。
  13. 如权要求10所述的无人飞行器，其特征在于，所述第一机壳包括多个凸肋，所述安装部形成有多个凸起，每个凸起开设有一个收容槽，每个所述收容槽用于收容一个所述凸肋。
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