WO2023046098A1 - 一种无人机 - Google Patents

一种无人机 Download PDF

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Publication number
WO2023046098A1
WO2023046098A1 PCT/CN2022/120988 CN2022120988W WO2023046098A1 WO 2023046098 A1 WO2023046098 A1 WO 2023046098A1 CN 2022120988 W CN2022120988 W CN 2022120988W WO 2023046098 A1 WO2023046098 A1 WO 2023046098A1
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WO
WIPO (PCT)
Prior art keywords
carbon fiber
arm
fuselage
unmanned aerial
aerial vehicle
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PCT/CN2022/120988
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English (en)
French (fr)
Inventor
黄昶
廖岳龙
Original Assignee
深圳市道通智能航空技术股份有限公司
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Publication of WO2023046098A1 publication Critical patent/WO2023046098A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • 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
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/08—Arrangements of cameras

Definitions

  • the embodiment of the utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.
  • the unmanned aircraft is referred to as "UAV", the English name is Unmanned Aerial Vehicle, and the English abbreviation is "UAV".
  • An unmanned aerial vehicle is an unmanned aircraft operated by radio remote control equipment and self-contained program control device, or an unmanned aircraft completely or intermittently operated autonomously by an on-board computer. UAVs are currently widely used in aerial photography, agriculture, plant protection, micro-selfies, express transportation, disaster relief, observing wild animals, monitoring infectious diseases, surveying and mapping, news reports, power inspections, disaster relief, film and television shooting, etc.
  • the unmanned aerial vehicle includes a fuselage, an arm and a wing.
  • the camera is provided with a pan-tilt for shooting, and the wing is connected to the fuselage through the arm.
  • various parts of drones are usually made of plastic.
  • the inventors of the present utility model found in the process of realizing the present utility model that the parts of the existing unmanned aerial vehicle are made of plastic, and when the parts of the unmanned aerial vehicle are easily rubbed or scratched Leave scratches.
  • the technical problem mainly solved by the embodiment of the utility model is to provide a carbon fiber texture structure, which can cover the surface of parts by carbon fiber texture, improve the scratch resistance of the surface of UAV parts, and greatly reduce the production time of UAV parts. And damage to the body caused by friction, scratches, etc. during use.
  • an unmanned aerial vehicle comprising:
  • one end of the arm is connected to the fuselage
  • the wings are mounted on the driving device, and the driving device is used to drive the wings to rotate;
  • the surface of at least one of the fuselage, the arm or the wings is provided with a carbon fiber texture layer.
  • the carbon fiber textured layer is integrally formed with the fuselage, arm or wing.
  • the carbon fiber texture layer has a texture width ranging from 0.01 mm to 0.05 mm.
  • the carbon fiber texture layer is printed on the surface of the fuselage, arm or wing by photocuring transfer printing process.
  • the carbon fiber texture layer is printed on the surface of the fuselage, arm or wing by a water transfer printing process.
  • the carbon fiber texture layer is coated on the surface of at least one of the fuselage, arm or wing by an in-mold insert injection molding process.
  • the drone further includes a paint layer, and the paint layer is applied to the carbon fiber texture layer.
  • the thickness of the paint layer is smaller than that of the carbon fiber texture layer.
  • the body includes a control assembly and a battery
  • the body is provided with a placement cavity
  • the control assembly and the battery are accommodated in the placement cavity
  • the battery is respectively connected to the control assembly and the drive device
  • the battery is used to supply power to the control assembly and the driving device
  • the control assembly is connected to the drive assembly.
  • the UAV also includes a cloud platform and a camera assembly, the cloud platform is fixed on the fuselage, the camera assembly is arranged on the cloud platform, and the cloud platform is used to control the camera assembly Rotate, both the camera assembly and the pan/tilt are electrically connected to the control assembly, wherein a part of the housing surface of the pan/tilt is provided with a carbon fiber texture layer.
  • the scratch resistance of the surface of the drone parts is improved. sex.
  • Fig. 1 is the overall schematic diagram of the utility model unmanned aerial vehicle embodiment
  • Fig. 2 is another schematic diagram of the utility model unmanned aerial vehicle embodiment
  • Fig. 3 is a schematic diagram of the connection relationship of an embodiment of the utility model unmanned aerial vehicle
  • Fig. 4 is the fuselage schematic diagram of the utility model unmanned aerial vehicle embodiment
  • Fig. 5 is a schematic diagram of another perspective of Fig. 4.
  • Fig. 6 is the sectional view of the fuselage of the utility model unmanned aerial vehicle embodiment
  • Fig. 7 is an exploded schematic diagram of the arm, the rotating assembly and the wings of the embodiment of the drone of the present invention.
  • the utility model provides an embodiment of an unmanned aerial vehicle. Please refer to FIGS. 1 to 3 .
  • One end is rotatably mounted on the fuselage 10
  • the drive device 30 is mounted on the other end of the arm
  • the wings 40 are mounted on the drive device 30, and the drive device 30 is used to drive the wings 40 for rotation.
  • the battery 12 is respectively connected to the control assembly 11 and the drive device 30, the battery 12 is used to supply power to the control assembly 11 and the drive device 30, and the control assembly 11 is connected to the drive components.
  • the control assembly 11 is composed of electronic components such as MCU, and the control assembly 11 includes a bluetooth module or a wireless module, and the control assembly 11 can be connected with an external device through the bluetooth module or a wireless module.
  • the control component 11 is controlled, so that the drone 1 has the capability of remote control.
  • one end of the fuselage 10 is provided with a first heat dissipation hole 102, the first heat dissipation hole 102 communicates with the placement cavity 101, and the first heat dissipation hole 102 is used for being accommodated in the placement cavity 101
  • the battery 12 and the control assembly 11 inside are dissipated, thereby reducing the heat emitted by the battery 12 and the control assembly 11 of the drone 1 during flight shooting, thereby prolonging the service life of the drone 1 .
  • the other end of the fuselage 10 facing the first heat dissipation hole 102 is provided with a second heat dissipation hole 103, and the second heat dissipation hole 103 communicates with the placement cavity 101. Convection is formed between the second heat dissipation hole 103 and the first heat dissipation hole 102, so that the air can better take away the heat dissipated by the battery 12 and the circuit assembly in the placement cavity 101, further The time for heat to stay in the placement cavity 101 is reduced, and the heat dissipation efficiency of the drone 1 is improved.
  • the UAV 1 also includes a cloud platform 50 and a camera assembly 60, the cloud platform 50 is fixed on the fuselage 10, the camera assembly 60 is arranged on the cloud platform 50, and the cloud platform 50 is used to control the rotation of the camera assembly 60.
  • Both the camera assembly 60 and the pan/tilt 50 are electrically connected to the control assembly 11, wherein a part of the shell surface of the pan/tilt 50 is provided with a carbon fiber texture layer.
  • the camera component 60 is a camera.
  • the outer surface of the fuselage 10 is provided with a carbon fiber texture layer
  • the fuselage 10 provided with a carbon fiber texture layer can reduce the damage of the fuselage due to external factors such as sand and dust during flight. 10 scratches, and the shell provided with the carbon fiber texture layer can improve the visual presentation effect of the product appearance, making the UAV 1 look more metallic.
  • the machine arm 20 includes a first connecting arm 201 , a second connecting arm 202 , a third connecting arm 203 and a fourth connecting arm 204 .
  • the fuselage 10 is provided with a first rotation groove 104, a second rotation groove 105, a third rotation groove 106 and a fourth rotation groove 107, a first rotation shaft 1041 is arranged in the first rotation groove 104, and a first rotation shaft 1041 is arranged in the first rotation groove 104.
  • the second rotating shaft 1051 is disposed in the second rotating groove 105
  • the third rotating shaft 1061 is disposed in the third rotating groove 106
  • the fourth rotating shaft 1071 is disposed in the fourth rotating groove 107 .
  • One end of the first connecting arm 201 is provided with a first rotating hole 2011, one end of the second connecting arm 202 is provided with a second rotating hole 2021, and one end of the third connecting arm 203 is provided with a third rotating hole 2031 , one end of the fourth connecting arm 204 is provided with a fourth rotation hole 2041 .
  • the first rotating shaft 1041 is accommodated in the first rotating hole 2011, and the first connecting arm 201 can rotate around the The first rotating shaft 1041 rotates.
  • the second connecting arm 202 When one end of the second connecting arm 202 is received in the second rotating groove 105, the second rotating shaft 1051 is received in the second rotating hole 2021, and the second rotating shaft 1051 is received in the second rotating hole 2021.
  • the two connecting arms 202 can rotate around the second rotating shaft 1051.
  • the third connecting arm 203 When one end of the third connecting arm 203 is accommodated in the third rotating groove 106, the third rotating shaft 1061 is accommodated in the third rotating shaft 1061.
  • Rotation hole 2031, the third connecting arm 203 can rotate around the third rotating shaft 1061, when one end of the fourth connecting arm 204 is accommodated in the fourth rotating groove 107, the fourth rotating shaft 1071 is accommodated in the fourth rotation hole 2041 , and the fourth connecting arm 204 can rotate around the fourth rotation axis 1071 .
  • At least one of the first connecting arm 201, the second connecting arm 202, the third connecting arm 203 or the fourth connecting arm 204 is provided with a carbon fiber texture layer on the surface, and the carbon fiber texture layer is compatible with the The first connecting arm 201 , the second connecting arm 202 , the third connecting arm 203 or the fourth connecting arm 204 are integrally formed.
  • the first connecting arm 201, the second connecting arm 202, the third connecting arm 203 and the fourth connecting arm 204 are in the unfolded state during the flight of the UAV 1, the first connecting arm 201, The second connecting arm 202, the third connecting arm 203, and the fourth connecting arm 204 are easy to collide with the external environment, such as: sand and dust scraping, etc., so they are arranged on the first connecting arm 201, the second connecting arm 202, the The carbon fiber texture layer on the third connecting arm 203 or the fourth connecting arm 204 can greatly reduce the scratches caused by the external environment on the first connecting arm 201 , the second connecting arm 202 , the third connecting arm 203 or the fourth connecting arm 204 .
  • the number of the driving device 30 and the number of the fins 40 are four, and the four driving devices 30 are respectively electrically connected with the control assembly 11, and one of the fins 40 is mounted on One of the driving devices 30 .
  • the other end of the first connecting arm 201 is provided with a first mounting cavity 2012
  • the other end of the second connecting arm 202 is provided with a second mounting cavity 2022
  • the other end of the third connecting arm 203 is provided with a third
  • the installation cavity 2032, the other end of the fourth connecting arm 204 is provided with a fourth installation cavity 2042
  • the four driving devices 30 are respectively installed in the first installation cavity 2012, the second installation cavity 2022, and the third installation cavity 2032 and the fourth installation cavity 2042.
  • first connecting arm 201, the second connecting arm 202, the third connecting arm 203 and the fourth connecting arm 204 are all provided with connecting channels (not shown in the figure), installed in the first installation cavity 2012, the second The driving device 30 in the installation cavity 2022 , the third installation cavity 2032 or the fourth installation cavity 2042 is respectively connected to the control assembly 11 and the battery 12 in the placement cavity 101 through the connection channel by wires.
  • the user rotates the first connecting arm 201, the second connecting arm 202, the third connecting arm 203 and the fourth connecting arm 204 to the preset operation position, and then
  • the driving device 30 is controlled to rotate by an external device, and the driving device 30 drives the wings 40 to rotate, so that the UAV 1 can take off from the ground and take aerial photography.
  • the fuselage 10, the arm 20, the wings 40, and the shell of the platform 50 are all made of plastic, and the fuselage 10 and the arm 20 made of plastic
  • the shells of the wings 40 and the pan/tilt 50 not only ensure the structural strength of the UAV 1 but also take into account the economy of the UAV 1 while satisfying the lightweight of the UAV 1 .
  • the carbon fiber texture layer on the fuselage 10, the machine arm 20, the wings 40, or the part shell of the platform 50 is connected with the body 10, the machine arm 20, the wings 40 or the cloud platform. Part of the shell of table 50 is integrally formed.
  • the preparation process is as follows: engraving carbon fiber lines on the injection mold by laser 3D, and then pouring the plastic into the mold until the plastic in the mold is molded and cooled and demoulded. After demoulding, the The fuselage 10, the arm 20 or the wings 40 are formed and a carbon fiber texture layer is formed on the surface. Due to the high precision of laser 3D engraving, the precision of the carbon fiber texture engraved on the mold can be controlled within 0.01mm to 0.05mm. The specific value varies according to different requirements. Therefore, the texture width of the carbon fiber texture layer on the surface of the fuselage 10, arm 20 or wing 40 integrally formed by this process can reach an accuracy of 0.01 mm.
  • the mold with 3D engraved carbon fiber texture compared with the existing mold without carbon fiber texture, can greatly reduce the plastic part's separation from the inner wall of the mold caused by cold shrinkage in the later stage of plastic molding in the mold, resulting in mold release.
  • the surface of the finished plastic part is partially matte, and the rest is bright, which improves the yield rate of the fuselage 10, the arm 20 or the wing 40.
  • one of the parts can be selected in the fuselage 10, the arm 20 or the wing 40, and a carbon fiber texture layer is set on the part, or, also Two of the parts can be selected in the fuselage 10, the machine arm 20 or the wing 40, and a carbon fiber texture layer is arranged on these two parts, or the surface of the fuselage 10, the machine arm 20 and the wing 40 All set carbon fiber texture layers.
  • the carbon fiber texture layer is coated on the surface of the fuselage 10 , the arm 20 or the wing 40 by a water transfer printing process.
  • the carbon fiber texture layer is coated on the surface of the fuselage 10, the arm 20 or the wing 40 by an in-mold insert injection molding process (IML process), that is, the printed Film
  • IML process in-mold insert injection molding process
  • the film is made into a carbon fiber shape, installed in an injection molding machine and an injection mold, and carbon fiber lines can be formed on the surface of the fuselage 10, machine arm 20 or wing 40 after injection molding in the mold.
  • the carbon fiber texture layer on the fuselage 10, the arm 20 or the wings 40 can be prepared by the processes mentioned in the above embodiments, including but not limited to the processes mentioned above, the carbon fiber texture
  • the layer can also be disposed on the surface of the fuselage 10 , the arm 20 or the wing 40 through an in-mold decoration process (IMD), a photocuring transfer process, or a de-plating process (PPVD).
  • IMD in-mold decoration process
  • PSVD de-plating process
  • the carbon fiber texture layer of the fuselage 10 , the arm 20 or the wings 40 is further coated with a paint layer, and the thickness of the paint layer is smaller than that of the carbon fiber texture layer.
  • the fuselage 10, machine arm 20 or wing 40 coated with paint and the carbon fiber texture layer can make the fuselage 10, machine arm 20 or wing 40 have a more metallic texture and improve the unmanned Machine 1 visual effects.
  • the scratch resistance of the surface of the drone parts is greatly improved .

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Abstract

一种无人机（1），无人机（1）包括：机身（10）；机臂（20），机臂（20）的一端与机身（10）连接；驱动装置（30），安装于机臂（20）的另一端；翼片（40），安装于驱动装置（30），驱动装置（30）用于驱动翼片（40）转动；其中，机身（10）、机臂（20）、翼片（40）或云台（50）部分壳体中的至少一个的表面设置有碳纤维纹理层。

Description

一种无人机
本申请要求于2021年9月24日提交中国专利局、申请号为2021223270833、申请名称为“一种无人机”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。
技术领域
本实用新型实施例涉及无人机技术领域，特别是涉及一种无人机。
背景技术
无人驾驶飞机简称“无人机”，英文名称为Unmanned Aerial Vehicle，英文缩写为“UAV”。无人机是利用无线电遥控设备和自备的程序控制装置操纵的不载人飞机，或者由车载计算机完全地或间歇性地自主操作的不载人飞机。无人机目前在航拍、农业、植保、微型自拍、快递运输、灾难救援、观察野生动物、监控传染病、测绘、新闻报道、电力巡检、救灾、影视拍摄等等领域均有广泛应用。无人机包括机身、机臂以及翼片，机身上设置有进行拍摄的云台，翼片通过机臂连接机身。为了满足轻量化以及低成本的需求，无人机的各个部件通常采用塑料制备而成。
但是本实用新型的发明人在实现本实用新型的过程中发现，现有无人机的零部件由于是采用的是塑料制备而成，当无人机的零部件在受到摩擦或者刮蹭之后容易留下划痕。
实用新型内容
本实用新型实施例主要解决的技术问题是提供一种碳纤维纹理结构，通过碳纤维纹理来覆盖零部件表面，提高了无人机零部件表面的耐刮性能，大幅降低了无人机零部件在生产及使用过程中因为摩擦、刮蹭等造成的机体损伤。
为解决上述技术问题，本实用新型采用的一个技术方案是：提供一种无人机，包括：
机身；
机臂，所述机臂的一端与所述机身连接；
驱动装置，安装于所述机臂的另一端；
翼片，安装于所述驱动装置，所述驱动装置用于驱动所述翼片转动；
其中，所述机身、机臂或翼片中的至少一个的表面设置有碳纤维纹理层。
可选的，所述碳纤维纹理层与所述机身、机臂或翼片一体成型。
可选的，所述碳纤维纹理层的纹理宽度范围处于0.01毫米至0.05毫米之间。
可选的，所述碳纤维纹理层由光固化转印工艺印制于所述机身、机臂或翼片的表面。
可选的，所述碳纤维纹理层由水转印工艺印制于所述机身、机臂或翼片的表面。
可选的，所述碳纤维纹理层由模内镶件注塑工艺涂覆于所述机身、机臂或翼片中的至少一个的表面。
可选的，所述无人机还包括漆层，所述漆层涂覆于所述碳纤维纹理层。
可选的，所述漆层的厚度小于所述碳纤维纹理层的厚度。
可选的，所述机身包括控制组件和电池，所述机身设置有放置腔，所述控制组件和所述电池收容于所述放置腔内，所述电池分别连接所述控制组件和驱动装置，所述电池用于给控制组件和驱动装置供电，所述控制组件连接所述驱动组件。
可选的，所述无人机还包括云台和摄像组件，所述云台固定于所述机身，所述摄像组件设置于所述云台，所述云台用于控制所述摄像组件转动，所述摄像组件和所述云台均与所述控制组件电性连接，其中，所述云台的部分壳体表面设置有碳纤维纹理层。
在本实用新型实施例中，通过在无人机的机身、机臂、翼片或云台的部分壳体中的至少一个的表面设置碳纤维纹理层，提高无人机零部件表面的耐刮性。
附图说明
图1是本实用新型无人机实施例的整体示意图；
图2是本实用新型无人机实施例的另一示意图；
图3是本实用新型无人机实施例的连接关系示意图；
图4是本实用新型无人机实施例的机身示意图；
图5是图4的另一视角示意图；
图6是本实用新型无人机实施例的机身剖断图；
图7是本实用新型无人机实施例的机臂、转动组件和翼片的爆炸示意图。
具体实施方式
为了便于理解本实用新型，下面结合附图和具体实施例，对本实用新型进行更详细的说明。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”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实用新型的技术领域的技术人员通常理解的含义相同。本说明书中在本实用新型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，不是用于限制本实用新型。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。
本实用新型提供一种无人机实施例，请参阅图1至图3，所述无人机1包括：机身10、机臂20、驱动装置30和翼片40，所述机臂20的 一端转动安装于所述机身10，所述驱动装置30安装于所述机臂的另一端，所述翼片40安装于所述驱动装置30，所述驱动装置30用于驱动所述翼片40进行转动。
对于上述机身10，请参阅图4-图6，所述机身10包括控制组件11和电池12，所述机身10设置有放置腔101，所述控制组件11和所述电池12收容于所述放置腔101内，所述电池12分别连接所述控制组件11和驱动装置30，所述电池12用于给所述控制组件11和驱动装置30供电，所述控制组件11连接所述驱动组件。其中，所述控制组件11是由MCU等电子元器件组成的，所述控制组件11包括蓝牙模块或者无线模块，所述控制组件11能够通过蓝牙模块或者无线模块与外部设备连接，用户通过外部设备对所述控制组件11进行操控，由此所述无人机1具备远程操控的性能。
具体的，所述机身10的一端设置有第一散热孔102，所述第一散热孔102与所述放置腔101连通，所述第一散热孔102用于供收容于所述放置腔101内的电池12以及控制组件11进行散热，从而降低所述无人机1在飞行拍摄过程中所述电池12以及所述控制组件11散发的热量，进而延长所述无人机1的使用寿命。
进一步的，所述机身10与所述第一散热孔102相向的另一端设置有第二散热孔103，所述第二散热孔103与所述放置腔101连通，由此，外部空气在所述第二散热孔103与所述第一散热孔102之间形成对流，从而能够更好的让空气带走所述电池12以及所述电路组件散发在所述放置腔101内的热量，进一步的减少热量留存于所述放置腔101内的时间，提高了所述无人机1的散热效率。
可选的，所述无人机1还包括云台50和摄像组件60，所述云台50固定于所述机身10，所述摄像组件60设置于所述云台50，所述云台50用于控制所述摄像组件60转动，所述摄像组件60和所述云台50均与所述控制组件11电性连接，其中，云台50的部分壳体表面设置有碳纤维纹理层。
在一些实时例中，所述摄像组件60为摄像头。
在本实用新型实施例中，所述机身10的外表面设置有碳纤维纹理层，设置有碳纤维纹理层的所述机身10能够在飞行过程中减少因为沙尘等外界因素导致所述机身10刮伤的情况，并且设置有碳纤维纹理层的所述外壳能够提升产品外观的视觉呈现效果，使所述无人机1看起来更具金属质感。
对于上述机臂20，请参阅图4、图5和图7，所述机臂20包括第一连接臂201、第二连接臂202、第三连接臂203和第四连接臂204。所述机身10设置有第一转动槽104、第二转动槽105、第三转动槽106和第四转动槽107，所述第一转动槽104内设置有第一转动轴1041，所述第二转动槽105内设置有第二转动轴1051，所述第三转动槽106内设置有第三转动轴1061，所述第四转动槽107内设置有第四转动轴1071。所述第一连接臂201的一端设置有第一转动孔2011，所述第二连接臂202的一端设置有第二转动孔2021，所述第三连接臂203的一端设置有第三转动孔2031，所述第四连接臂204的一端设置有第四转动孔2041。当所述第一连接臂201的一端收容于所述第一转动槽104内时，所述第一转动轴1041收容于所述第一转动孔2011内，所述第一连接臂201可绕所述第一转动轴1041转动，当所述第二连接臂202的一端收容于所述第二转动槽105内时，所述第二转动轴1051收容于所述第二转动孔2021，所述第二连接臂202可绕所述第二转动轴1051转动，当所述第三连接臂203的一端收容于所述第三转动槽106内时，所述第三转动轴1061收容于所述第三转动孔2031，所述第三连接臂203可绕所述第三转动轴1061转动，当所述第四连接臂204的一端收容于所述第四转动槽107内时，所述第四转动轴1071收容于所述第四转动孔2041，所述第四连接臂204可绕所述第四转动轴1071转动。
在一些实施例中，所述第一连接臂201、第二连接臂202、第三连接臂203或第四连接臂204中，至少一个的表面设置有碳纤维纹理层，所述碳纤维纹理层与所述第一连接臂201、第二连接臂202、第三连接臂203或第四连接臂204一体成型。由于所述第一连接臂201、第二连接臂202、第三连接臂203以及第四连接臂204在所述无人机1的飞行 过程中处于展开状态，因此所述第一连接臂201、第二连接臂202、第三连接臂203以及第四连接臂204容易与外部环境发生碰撞，例如：沙尘刮擦等，因此设置于所述第一连接臂201、第二连接臂202、第三连接臂203或第四连接臂204上的碳纤维纹理层能够大幅减少外部环境对所述第一连接臂201、第二连接臂202、第三连接臂203或第四连接臂204造成的划痕。
对于上述驱动装置30，所述驱动装置30和所述翼片40的数量均为四个，四个所述驱动装置30分别与所述控制组件11电性连接，一所述翼片40安装于一所述驱动装置30上。所述第一连接臂201的另一端设置有第一安装腔2012，所述第二连接臂202的另一端设置有第二安装腔2022，所述第三连接臂203的另一端设置有第三安装腔2032，所述第四连接臂204的另一端设置有第四安装腔2042，四个所述驱动装置30分别安装于所述第一安装腔2012、第二安装腔2022、第三安装腔2032以及第四安装腔2042内。其中所述第一连接臂201、第二连接臂202、第三连接臂203以及第四连接臂204均设置有连接通道(图未示出)，安装于所述第一安装腔2012、第二安装腔2022、第三安装腔2032或第四安装腔2042内的驱动装置30由导线通过所述连接通道分别与放置腔101内的所述控制组件11以及电池12连接。当所述无人机1需要进行飞行作业时，用户分别将所述第一连接臂201、第二连接臂202、第三连接臂203以及第四连接臂204转动至预设作业工位，然后通过外部设备操控所述驱动装置30进行转动，所述驱动装置30带动所述翼片40旋转，由此所述无人机1能够从地面起飞并进行航拍。
在本实用新型实施例中，所述机身10、机臂20、翼片40以及云台50部分壳体均由塑料制备而成，由塑料制备而成的所述机身10、机臂20、翼片40以及云台50部分壳体在满足无人机1轻量化的同时既保证了无人机1的结构强度还兼顾了无人机1的经济性。在本实用新型实施例中，所述机身10、机臂20、翼片40、或者云台50部分壳体上的碳纤维纹理层与所述机身10、机臂20、翼片40或者云台50部分壳体一体成型，其制备工艺为：通过激光3D在注塑磨具上雕刻碳纤维纹路，然 后将塑料浇筑至模具中直至位于模具内的塑料成型冷却后脱模，脱模后的所述机身10、机臂20或者翼片40成型并且在其表面形成有碳纤维纹理层，由于激光3D雕刻的精度较高，因此雕刻在模具上的碳纤维纹路的精度能够控制在0.01mm至0.05mm之间，具体的数值根据不同的需求变化，因此，通过该工艺一体成型的所述机身10、机臂20或者翼片40表面的碳纤维纹理层的纹理宽度能够达到0.01mm的精度。另外，具有3D雕刻碳纤维纹路的模具，相比于现有没有碳纤维纹路的模具，能够使塑料在模具中成型的后期大幅减少注塑件因为冷缩导致的塑料与模具内壁局部脱离，造成成型脱模后的塑料件表面局部呈哑光色泽，其余呈亮光色泽的情况，提高了所述机身10、机臂20或者翼片40的良品率。
值得说明的是，根据无人机1产品的作业环境考虑，可以在所述机身10、机臂20或者翼片40中选择其中的一个部件，在该部件上设置碳纤维纹理层，或者，也可以在所述机身10、机臂20或者翼片40中选择其中两个部件，在这两个部件上设置碳纤维纹理层，又或者所述机身10、机臂20和翼片40的表面全部设置碳纤维纹理层。
在一些实施例中，所述碳纤维纹理层由水转印工艺涂覆于所述机身10、机臂20或翼片40的表面。
在一些别的实施例中，所述碳纤维纹理层由模内镶件注塑工艺(IML工艺)涂覆于所述机身10、机臂20或翼片40的表面，即：把印刷好的Film薄膜制作成碳纤维状，安装到注塑机和注塑模具内，在机身10、机臂20或翼片40在模具内注塑成型后就能在其表面形成碳纤维纹路。
值得说明的是，所述机身10、机臂20或翼片40上的碳纤维纹理层可以由上述实施例中提及的工艺制备得到，包括但不仅限于上述提及的工艺，所述碳纤维纹理层还可以是通过模内装饰工艺(IMD)、光固化转印工艺或者退镀工艺(PPVD)等设置于所述机身10、机臂20或翼片40的表面。
在一些其他的实施例中，所述机身10、机臂20或翼片40的碳纤维纹理层上还涂覆有漆层，所述漆层的厚度小于所述碳纤维纹理层的厚度。经过漆层涂覆的所述机身10、机臂20或翼片40搭配所述碳纤维纹理层 能够使所述机身10、机臂20或翼片40更具金属质感，提升所述无人机1的视觉效果。
本实用新型实施例中，通过在无人机1的机身10、机臂20或翼片40中的至少一个的表面设置碳纤维纹理层，使无人机零部件表面的耐刮性大幅度提高。
需要说明的是，本实用新型的说明书及其附图中给出了本实用新型的较佳的实施例，但是，本实用新型可以通过许多不同的形式来实现，并不限于本说明书所描述的实施例，这些实施例不作为对本实用新型内容的额外限制，提供这些实施例的目的是使对本实用新型的公开内容的理解更加透彻全面。并且，上述各技术特征继续相互组合，形成未在上面列举的各种实施例，均视为本实用新型说明书记载的范围；进一步地，对本领域普通技术人员来说，可以根据上述说明加以改进或变换，而所有这些改进和变换都应属于本实用新型所附权利要求的保护范围。

Claims (10)

  1. 一种无人机，其特征在于，包括：
    机身；
    机臂，所述机臂的一端与所述机身连接；
    驱动装置，安装于所述机臂的另一端；
    翼片，安装于所述驱动装置，所述驱动装置用于驱动所述翼片转动；
    其中，所述机身、机臂或翼片中的至少一个的表面设置有碳纤维纹理层。
  2. 根据权利要求1所述的无人机，其特征在于，
    所述碳纤维纹理层与所述机身、机臂或翼片一体成型。
  3. 根据权利要求2所述的无人机，其特征在于，
    所述碳纤维纹理层的纹理宽度范围处于0.01毫米至0.05毫米之间。
  4. 根据权利要求1所述的无人机，其特征在于，
    所述碳纤维纹理层由光固化转印工艺印制于所述机身、机臂或翼片的表面。
  5. 根据权利要求1所述的无人机，其特征在于，
    所述碳纤维纹理层由水转印工艺印制于所述机身、机臂或翼片的表面。
  6. 根据权利要求1所述的无人机，其特征在于，
    所述碳纤维纹理层由模内镶件注塑工艺涂覆于所述机身、机臂或翼片中的至少一个的表面。
  7. 根据权利要求1所述的无人机，其特征在于，还包括漆层，所述 漆层涂覆于所述碳纤维纹理层。
  8. 根据权利要求7所述的无人机，其特征在于，
    所述漆层的厚度小于所述碳纤维纹理层的厚度。
  9. 根据权利要求1所述的无人机，其特征在于，
    所述机身包括控制组件和电池，所述机身设置有放置腔，所述控制组件和所述电池收容于所述放置腔内，所述电池分别连接所述控制组件和驱动装置，所述电池用于给控制组件和驱动装置供电，所述控制组件连接所述驱动组件。
  10. 根据权利要求9所述的无人机，其特征在于，
    所述无人机还包括云台和摄像组件，所述云台固定于所述机身，所述摄像组件设置于所述云台，所述云台用于控制所述摄像组件转动，所述摄像组件和所述云台均与所述控制组件电性连接，其中，所述云台的部分壳体表面设置有碳纤维纹理层。
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH091681A (ja) * 1995-06-21 1997-01-07 Fuji Heavy Ind Ltd 繊維強化複合材の構造体及びその製造方法
CN206416950U (zh) * 2017-01-03 2017-08-18 北京汽车股份有限公司 装饰板和具有其的车辆
CN108215413A (zh) * 2017-12-29 2018-06-29 江苏澳盛复合材料科技有限公司 全表面具有编织纹理的可再塑型碳纤维板材及其制备方法
CN113733451A (zh) * 2021-09-24 2021-12-03 深圳市道通智能航空技术股份有限公司 碳纤维纹理配件的制备方法、碳纤维纹理配件和无人机
CN216301443U (zh) * 2021-09-24 2022-04-15 深圳市道通智能航空技术股份有限公司 一种无人机

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH091681A (ja) * 1995-06-21 1997-01-07 Fuji Heavy Ind Ltd 繊維強化複合材の構造体及びその製造方法
CN206416950U (zh) * 2017-01-03 2017-08-18 北京汽车股份有限公司 装饰板和具有其的车辆
CN108215413A (zh) * 2017-12-29 2018-06-29 江苏澳盛复合材料科技有限公司 全表面具有编织纹理的可再塑型碳纤维板材及其制备方法
CN113733451A (zh) * 2021-09-24 2021-12-03 深圳市道通智能航空技术股份有限公司 碳纤维纹理配件的制备方法、碳纤维纹理配件和无人机
CN216301443U (zh) * 2021-09-24 2022-04-15 深圳市道通智能航空技术股份有限公司 一种无人机

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"Master's Thesis", 1 June 2019, CHANGCHUN INDUSTRIAL COLLEGE, China, article SANG, YANQING: "Research on the Design of the Drone for Marine Search and Rescue", pages: 1 - 63, XP009544854 *

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