WO2019024806A1 - 无人机 - Google Patents

无人机 Download PDF

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Publication number
WO2019024806A1
WO2019024806A1 PCT/CN2018/097543 CN2018097543W WO2019024806A1 WO 2019024806 A1 WO2019024806 A1 WO 2019024806A1 CN 2018097543 W CN2018097543 W CN 2018097543W WO 2019024806 A1 WO2019024806 A1 WO 2019024806A1
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WO
WIPO (PCT)
Prior art keywords
circular arc
arc surface
fuselage
mounting
housing
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/CN2018/097543
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English (en)
French (fr)
Inventor
肖锭锋
徐智芹
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.)
Guangzhou Xaircraft Technology Co Ltd
Original Assignee
Guangzhou Xaircraft Technology Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Guangzhou Xaircraft Technology Co Ltd filed Critical Guangzhou Xaircraft Technology Co Ltd
Priority to EP18842282.8A priority Critical patent/EP3663189A4/en
Priority to CA3063253A priority patent/CA3063253A1/en
Priority to US16/609,038 priority patent/US20200156789A1/en
Priority to KR1020197035323A priority patent/KR102324542B1/ko
Priority to RU2019137310A priority patent/RU2719603C1/ru
Priority to AU2018310402A priority patent/AU2018310402B2/en
Priority to JP2019567348A priority patent/JP6853901B2/ja
Publication of WO2019024806A1 publication Critical patent/WO2019024806A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body
    • B64U20/75—Constructional aspects of the UAV body the body formed by joined shells or by a shell overlaying a chassis
    • 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
    • B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
    • B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
    • B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/06—Undercarriages fixed
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U60/00—Undercarriages
    • B64U60/50—Undercarriages with landing legs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/40—UAVs specially adapted for particular uses or applications for agriculture or forestry operations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/45—UAVs specially adapted for particular uses or applications for releasing liquids or powders in-flight, e.g. crop-dusting
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention belongs to the technical field of drones, and in particular relates to a drone.
  • a drone is a non-manned aerial vehicle that is controlled by a wireless remote control device and its own control device.
  • drones have been widely used in plant protection operations, for example, using drones.
  • Plant spraying and farming management of plants When a drone sprays a plant into a pharmaceutical industry, a liquid storage container is generally disposed on the body of the drone, and the liquid storage container is used to hold the liquid medicine to be sprayed.
  • UAVs used in plant protection operations generally include a fuselage, functional components mounted to the fuselage, such as a reservoir and a battery.
  • the layout of the fuselage structure of the drone is unreasonable, so that the drone has low work efficiency and high energy consumption.
  • the object of the present invention is to provide a drone, which aims to solve the problem that the existing drone layout is unreasonable, so that the drone has low work efficiency and high energy consumption.
  • a drone the body includes a fuselage body, the casing assembly is coupled to a front end of the fuselage body, and the functional component is mounted to the rear of the fuselage body
  • the upper end surface of the functional component is a first circular arc surface
  • the upper end surface of the housing assembly is a second circular arc surface, the first circular arc surface and the second circular arc surface are adjacent to each other, and The first circular arc surface and the second circular arc surface form a streamline curved surface.
  • the functional component includes a liquid storage container, the liquid storage container is mounted at a rear end of the fuselage body, and a top surface of the liquid storage container has a third circular arc surface, and the third circular arc surface is adjacent to The second arc surface, at least a portion of the first arc surface is the third arc surface.
  • the functional component further includes a battery component, the liquid storage container is located between the battery component and the housing component, and the top of the battery component has a fourth circular arc surface, the third circular arc The surface is located between the fourth circular arc surface and the second circular arc surface, and at least a portion of the first circular arc surface is the fourth circular arc surface.
  • the housing assembly includes a mounting housing that is coupled to the front end of the fuselage body and a base housing that is coupled to the mounting housing, and an upper end surface of the base housing is the second Arc surface.
  • the base housing includes a base case body coupled to the connecting beam and a top cover coupled to the base case body, the base case body including a front case and upward along the front case And an upper casing extending rearward, the top cover is disposed on the upper casing, and an upper end surface of the top cover and the upper casing forms the second circular arc surface.
  • the upper casing is provided with a mounting hole for positioning and connecting the top cover, and a matching groove for abutting against the inner wall of the top cover is formed on the periphery of the mounting hole, and the top cover is magnetic A suction connection is provided in the mating groove.
  • the front case extends rearward along both sides thereof and is formed with a ventilation duct that facilitates heat dissipation of the body body.
  • the liquid storage container includes a container body having a liquid storage chamber, the container body including a lower case and an upper case connected to an upper portion of the lower case, the upper case and the lower case The body is connected, the top of the upper case is the third circular arc surface, and the battery member is adjacent to an end of the upper case away from the housing assembly.
  • the airframe further includes a mounting frame, the mounting frame includes a mounting bracket connected to the rear end of the fuselage body, and a mounting bracket connected to the fixing bracket, wherein the mounting bracket is provided with the mounting bracket
  • the lower casing of the liquid storage container is connected to the first installation through groove of the limit, and the second mounting groove for limiting connection of the battery component is disposed in the mounting frame.
  • the fuselage body further has a plurality of arms extending outwardly, and the extending end of the arm is further provided with a power component, and the bottom of the fuselage body is further provided with a landing gear for buffering during landing. .
  • the housing assembly is disposed at the front end of the fuselage while the functional component is disposed at the rear end of the fuselage;
  • the upper end surface has a second circular arc surface, and the upper end surface of the functional component has a first circular arc surface, and the first circular arc surface and the second circular arc surface are adjacent to each other, and the first circular arc surface and the second circular arc surface
  • the surface forms a streamlined surface, which reduces the air resistance when the drone is working, thereby reducing energy consumption.
  • FIG. 1 is a schematic perspective structural view of a drone according to an embodiment of the present invention.
  • FIG. 2 is a schematic perspective view of the unmanned aerial vehicle of FIG. 1 with the battery removed.
  • FIG. 3 is a schematic perspective view showing a partial structure of the unmanned aerial vehicle of FIG. 1.
  • FIG. 4 is a perspective view showing the housing assembly of the unmanned aerial vehicle of FIG. 1.
  • Figure 5 is a perspective view of the housing assembly of Figure 4.
  • Figure 6 is a perspective view showing the structure of the liquid storage container of the unmanned aerial vehicle of Figure 1.
  • Figure 7 is a side elevational view of the drone of Figure 1.
  • 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” and “second” may include one or more of the features either explicitly or implicitly.
  • the meaning of "a plurality” is two or more unless specifically and specifically defined otherwise.
  • a drone including a body 1 and a housing assembly 3 and a functional component connected to the body 1 , the housing assembly 3 is attached to the body 1.
  • the fuselage 1 includes a fuselage body 10 and a mounting frame 14 attached to the fuselage body 10, the functional component being coupled to the mounting frame 14, and the functional component preferably includes a liquid storage container 6 and a battery component 7,
  • the liquid storage container 6 is for storing a liquid to be sprayed.
  • the housing assembly 3 includes a mounting housing 31 that is coupled to the main body 10 and a base housing 32 that is coupled to the mounting housing 31.
  • the mounting housing 31 and the base housing 32 are connected in an up-and-down relationship.
  • the liquid container 6 and the housing assembly 3 are coupled to the body 10 in a front-rear (or left-right) relationship.
  • the upper end surface of the liquid storage container 6 and/or the battery member 7 has a first circular arc surface
  • the upper end surface of the base housing 32 has a second circular arc surface
  • the first circular arc surface and the second circular arc surface Adjacent that is, one end of the first circular arc surface is in close contact with one end of the second circular arc surface
  • the first circular arc surface and the second circular arc surface form a streamline curved surface, where preferably
  • the first circular arc surface and the second circular arc surface are adjacent to each other to form a complete curved surface.
  • the drone designed above is provided with a mounting frame 14 on the fuselage 1, and the liquid storage container 6 can be detachably connected in the mounting frame 14, thereby realizing rapid rapid installation of the liquid storage container 6 on the main body of the body 1.
  • the arc faces are adjacent, and the first arc face and the second arc face form a streamline curved surface, thereby reducing air resistance when the drone is working, thereby reducing energy consumption.
  • the functional component is a component or a combination of several components that provide resources for the drone to implement various functions.
  • its volume is relatively large in the components of the drone.
  • the upper end surface of the functional component has a streamlined surface which can reduce the large resistance of the drone's flight.
  • the plant protection drone it can be the liquid storage container 6 or the battery unit 7, or both. .
  • the functional component includes a liquid storage container 6 mounted on a rear end of the fuselage body 10, and a top surface of the liquid storage container 6 has a third circular arc surface.
  • the third arc surface is adjacent to the second arc surface, and at least a portion of the first arc surface is the third arc surface.
  • the functional component further includes a battery member 7 adjacent to an end of the liquid storage container 6 away from the housing assembly 3, the top of the battery member 7 having a fourth circle a curved surface, the fourth circular arc surface is adjacent to an end of the third circular arc surface away from the second circular arc surface, and at least a portion of the first circular arc surface is the fourth circular arc surface.
  • the mounting housing 31 is fixedly coupled to the body 10, and the mounting housing 31 includes a plurality of connected to the body 10. a connecting shell (not shown) and a connecting beam connected between the plurality of connecting shells and supporting the base shell 32.
  • the number of the connecting shells is preferably two, and the connecting beam is connected to the two connecting shells.
  • the base housing 32 includes a base housing body 321 coupled to the connecting beam and a top cover 322 coupled to the base housing body 321.
  • the base housing body 321 includes a front housing 3211 and an upper housing 3212 extending upward and rearward along the front housing 3211, that is, the The front housing 3211 and the upper housing 3212 are integral, and the upper housing 3212 is located at an upper portion of the front housing 3211.
  • the top cover 322 is disposed on the upper housing 3212, and the top cover 322 and The upper end surface of the upper casing 3212 forms the second circular arc surface.
  • the upper casing 3212 is provided with a mounting hole 3213 for positioning and connecting the top cover 322.
  • the bottom surface of the top cover 322 extends downwardly with a positioning shaft for positioning and connecting on the mounting hole 3213.
  • the mounting hole 3213 is formed with a fitting groove 3214 for abutting against the inner wall of the top cover 322, and the top cover 322 is magnetically attracted and coupled in the fitting groove 3214.
  • a magnetic ring 3215 is disposed in the matching groove 3214.
  • the top cover 322 is pre-arranged with a metal magnetic conductive material, and the top cover 322 is firstly connected to the mounting hole 3213 through a positioning shaft. Pre-positioning, the top cover 322 is magnetically attracted to the magnetic ring 3215 such that the top cover 322 is coupled within the mating slot 3214.
  • the front case 3211 extends rearward along both sides thereof and forms a ventilation duct 3210 for facilitating heat dissipation of the body 10.
  • the ventilation duct 3210 is arranged such that when the drone is in operation, the air passes through the ventilation ducts 3210 on both sides, on the one hand, the heat dissipation of the fuselage body 10 can be enhanced, and the other convenience can also reduce the wind resistance of the windward side.
  • the battery frame 7 for supplying power to the body 10 is also connected to the mounting frame 14.
  • the mounting frame 14 includes a connection body and the body. a mounting bracket 141 on the main body and a mounting bracket 142 connected to the fixing bracket 141.
  • the mounting bracket 141 is provided with a first mounting through slot 144 for limitingly connecting the liquid storage container 6.
  • the mounting bracket 142 is provided There is a second mounting through groove 145 for limiting connection of the battery member 7.
  • a partition 143 is further connected between the fixing frame 141 and the mounting bracket 142 for separating the first mounting through groove 144 and the second mounting through groove 145.
  • the liquid storage container 6 includes a container body having a liquid storage cavity, and the container body includes a limit connection in the first installation through groove 144.
  • a case 62 and an upper case 61 connected to an upper portion of the lower case 62 for abutting against the body body 10 the upper case 61 and the lower case 62 are preferably perpendicular to each other, and the upper case 61
  • the lower case 62 constitutes a "T" type or an inverted “L” type.
  • the upper casing 61 and the lower casing 62 are in communication, so that the storage amount of the liquid in the liquid storage chamber can be ensured.
  • the upper casing 61 is further provided with a liquid inlet 616 for adding a liquid, and the liquid inlet 616 is also screwed with an end cover (not shown), and the lower portion of the upper casing 61 is The lower portion of the lower casing 62 is also provided with a liquid outlet 621 for spraying liquid.
  • the upper casing 61 includes a bottom wall 611, a side wall 612 connected to both sides of the bottom wall 611, and a top wall 613 connected to the top ends of the two side walls 612, and is connected to the bottom wall.
  • the front end wall 614 and the rear end wall 615 of the front and rear ends of the 611, the upper end surface of the top wall 613 is the third arc surface, and the lower box 62 extends downward along the bottom wall 611.
  • the lower case 62 passes through the first mounting through groove 144, and the upper case 61 abuts on the body body 10, thereby completing the connection of the liquid storage container 6.
  • the fuselage body 10 includes a top plate 12 connected to the mounting housing 31, a bottom plate 13 disposed opposite the top plate 12, and the top plate 12 and the A transfer bin 11 between the bottom plates 13 is connected to the control system.
  • the fuselage body 10 further extends outwardly with a plurality of arms 2, and the extended end of the arm 2 is further connected with a power component 5, A landing gear 4 for cushioning during landing is also attached to the bottom of the fuselage body 10.
  • an electric adjustment module is further connected to the body 1 , and the arm 2 is distributed around the body 10 , and the arm 2 is fixedly connected to the body 10 .
  • the landing gear 4 is fixed below the fuselage body 10 to ensure the stability of the drone take-off and landing.
  • the power component 5 is fixed to the end of the arm 2 away from the fuselage body 10, and the power component 5 is a drone.
  • the flight provides lift, the liquid storage container 6 is mounted on the fuselage 1 and is used to hold articles to be sprayed or to be transported, and the battery member 7 is fixed to the fuselage body 10 for supplying power to the fly-power assembly 5, and the control system is fixed.
  • the fuselage 1 is used to control the flight posture of the drone.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Mechanical Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Pest Control & Pesticides (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
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Abstract

一种无人机，包括机身（1）、壳体组件（3）和功能组件，所述机身包括机身本体（10），所述壳体组件（3）连接在所述机身本体的前端，所述功能组件安装于所述机身本体的后端，所述功能组件的上端面呈第一圆弧面，所述壳体组件（3）的上端面呈第二圆弧面，所述第一圆弧面和所述第二圆弧面相邻，且所述第一圆弧面和所述第二圆弧面构成流线曲面，这样设计可以解决现有的无人机布局不合理以致无人机工作效率低，能耗大的问题。

Description

无人机 技术领域
本发明属于无人机技术领域，尤其涉及一种无人机。
背景技术
无人机是指利用无线遥控设备和自身的控制装置进行控制的不载人飞行器，近年来，由于自动化技术水平的提高，无人机被广泛应用于植物保护作业中，例如，利用无人机对植物进行药液喷洒作业和农耕管理等。无人机对植物进行药业喷洒时，一般会在无人机的机身上设置储液容器，利用储液容器盛装待喷洒的药液。
应用于植物保护作业的无人机一般包括机身、安装于机身的功能组件，如储液容器和电池。相关技术公开的资料中，无人机的机身结构布局不合理以致无人机的工作效率低、能耗大。
发明内容
本发明的目的在于提供一种无人机，旨在解决现有的无人机布局不合理以致无人机工作效率低，能耗大的问题。
本发明是这样解决的：一种无人机，所述机身包括机身本体，所述壳体组件连接在所述机身本体的前端，所述功能组件安装于所述机身本体的后端，所述功能组件的上端面为第一圆弧面，所述壳体组件的上端面为第二圆弧面，所述第一圆弧面和所述第二圆弧面相邻，且所述第一圆弧面和所述第二圆弧面构成流线曲面。
进一步地，所述功能组件包括储液容器，所述储液容器安装于所述机身本体的后端，所述储液容器的顶部具有第三圆弧面，所述第三圆弧面邻近所述第 二圆弧面，所述第一圆弧面的至少一部分为所述第三圆弧面。
进一步地，所述功能组件还包括电池件，所述储液容器位于所述电池件和所述壳体组件之间，所述电池件的顶部具有第四圆弧面，所述第三圆弧面位于所述第四圆弧面和所述第二圆弧面之间，所述第一圆弧面的至少一部分为所述第四圆弧面。
进一步地，所述壳体组件包括限位连接在所述机身本体前端的安装壳体和连接在所述安装壳体上方的基壳体，所述基壳体的上端面为所述第二圆弧面。
进一步地，所述基壳体包括连接在所述连接梁上的基壳本体和连接在所述基壳本体上的顶盖，所述基壳本体包括前壳体和沿所述前壳体向上且向后延伸的上壳体，所述顶盖盖设在所述上壳体上，且所述顶盖和所述上壳体的上端面形成所述第二圆弧面。
进一步地，所述上壳体上设有供所述顶盖定位连接的安装孔，所述安装孔的周沿上形成有供与所述顶盖内壁抵接的配合槽，且所述顶盖磁性吸合连接在所述配合槽内。
进一步地，所述前壳体沿其两侧均向后延伸并形成有便于所述机身本体散热的通风涵道。
进一步地，所述储液容器包括具有储液腔体的容器主体，所述容器主体包括下箱体和连接在所述下箱体上部的上箱体，所述上箱体和所述下箱体连通，所述上箱体的顶部为所述第三圆弧面，所述电池件靠近所述上箱体远离所述壳体组件的一端。
进一步地，所述机身还包括安装框，所述安装框包括连接于所述机身本体后端的固定架和连接在所述固定架上的安装架，所述固定架内设有供所述储液容器的下箱体限位连接的第一安装通槽，所述安装架内设有供所述电池件限位连接的第二安装通槽。
进一步地，所述机身本体上还向外延伸有若干个机臂，所述机臂的延伸末端还设置有动力组件，所述机身本体的底部上还设置有用于起落时缓冲的起落 架。
本发明提供的无人机相对于现有的技术具有的技术效果为：通过将壳体组件设置在机身的前端，同时将功能组件设置在机身的后端；同时该壳体组件上的上端面呈第二圆弧面，该功能组件的上端面呈第一圆弧面，并且该第一圆弧面和第二圆弧面相邻，且该第一圆弧面和第二圆弧面构成流线曲面，从而减少无人机工作时的空气阻力，进而降低能耗。
附图说明
为了更清楚地说明本发明实施例中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。
图1是本发明实施例提供的无人机的立体结构示意图。
图2是图1中无人机去掉电池的立体结构示意图。
图3是图1中无人机的部分结构的立体结构示意图。
图4是图1中无人机的壳体组件的立体结构示意图。
图5是图4中壳体组件的立体结构示意图。
图6是图1中无人机的储液容器的立体结构示意图。
图7是图1中无人机的侧视图。
其中，1、机身；10、机身本体；11、中转仓；12、顶板；13、底板；14、安装框；141、固定架；142、安装架；143、隔板；144、第一安装通槽；145、第二安装通槽；
2、机臂；3、壳体组件；31、安装壳体；32、基壳体；321、基壳本体；322、顶盖；3211、前壳体；3212、上壳体；3213、安装孔；3214、配合槽；3215、磁环；3210、通风涵道；
4、起落架；5、动力组件；6、储液容器；61、上箱体；62、下箱体；611、 底壁；612、侧壁；613、顶壁；614、前端壁；615、后端壁；616、进液口；621、出液口；
7、电池件。
具体实施方式
为了使本发明的目的、技术方案及优点更加清楚明白，以下结合附图及实施例，对本发明进行进一步详细说明。应当理解，此处所描述的具体实施例仅仅用以解释本发明，并不用于限定本发明。
需要说明的是，当元件被称为“固定于”或“设置于”另一个元件，它可以直接在另一个元件上或者间接在该另一个元件上。当一个元件被称为是“连接于”另一个元件，它可以是直接连接到另一个元件或间接连接至该另一个元件上。
需要理解的是，术语“长度”、“宽度”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”“内”、“外”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该特征。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。
请参照附图1至图7所示，在本发明实施例中，提供一种无人机，包括机身1和连接在该机身1上的壳体组件3和功能组件，该壳体组件3盖设在该机身1上。该机身1包括机身本体10和连接在该机身本体10上的安装框14，该功能组件连接在该安装框14上，并且该功能组件优选为包括储液容器6和电池件7，该储液容器6用于存储待喷洒的液体。该壳体组件3包括限位连接在该机身本体10上的安装壳体31和连接在该安装壳体31上方的基壳体32，该安 装壳体31和基壳体32呈上下关系连接，该储液容器6和该壳体组件3呈前后(或左右)关系连接在该机身本体10上。该储液容器6和/或该电池件7的上端面呈第一圆弧面，该基壳体32的上端面呈第二圆弧面，该第一圆弧面和该第二圆弧面相邻，也即该第一圆弧面的一端与该第二圆弧面的一端贴合连接，并且该第一圆弧面和该第二圆弧面构成流线曲面，此处优选为该第一圆弧面和第二圆弧面相邻形成一个完整的弧面。
以上设计的无人机，通过在机身1上设置安装框14，进而储液容器6可以拆卸连接在该安装框14内，从而实现快速地将储液容器6在机身1主体上的快速安装和拆卸；同时该壳体组件3上的基壳体32上端面呈第二圆弧面，该储液容器6的上端面呈第一圆弧面，并且该第一圆弧面和第二圆弧面相邻，且该第一圆弧面和第二圆弧面构成流线曲面，从而减少无人机工作时的空气阻力，进而降低能耗。
在本实施例中，该功能组件是为无人机实现各种功能提供资源的部件或几个部件的组合，一般来说，它的体积在无人机的元件中相对较大。进而该功能组件的上端面呈流线曲面可以为无人机的飞行减去较大的阻力，例如在植保无人机中，它可以是储液容器6或者电池件7，或者两者都有。
具体地，在本发明实施例中，该功能组件包括储液容器6，该储液容器6安装于该机身本体10的后端，该储液容器6的顶部具有第三圆弧面，该第三圆弧面靠近该第二圆弧面，并且该第一圆弧面的至少一部分为该第三圆弧面。
当然，在还可以是在本实施例中，该功能组件还包括电池件7，该电池件7靠近该储液容器6远离该壳体组件3的一端，该电池件7的顶部具有第四圆弧面，该第四圆弧面靠近该第三圆弧面的远离该第二圆弧面的一端，同样该第一圆弧面的至少一部分为该第四圆弧面。
具体地，如图2至图5所示，在本发明实施例中，该安装壳体31固定连接在机身本体10上，同时该安装壳体31包括连接在该机身本体10上的多个连接壳(图未示)和连接在多个该连接壳之间并用于支撑该基壳体32的连接梁，该 连接壳的数量优选为两个，该连接梁连接在两个该连接壳之间，该基壳体32包括连接在该连接梁上的基壳本体321和连接在该基壳本体321上的顶盖322。
具体地，如图4和图5所示，在本发明实施例中，该基壳本体321包括前壳体3211和沿该前壳体3211向上且向后延伸的上壳体3212，也即该前壳体3211和上壳体3212是一体的，并且该上壳体3212是位于该前壳体3211的上部的，该顶盖322盖设在该上壳体3212上，并且该顶盖322和该上壳体3212的上端面形成该第二圆弧面。
在本发明实施例中，该上壳体3212上设有供该顶盖322定位连接的安装孔3213，该顶盖322的底面向下延伸有供定位连接在该安装孔3213上的定位轴(图未示)，同时该安装孔3213的周沿上形成有供与该顶盖322内壁抵接的配合槽3214，并且该顶盖322磁性吸合连接在该配合槽3214内。
在本实施例中，该配合槽3214内预先设置有磁环3215，该顶盖322上预设有金属导磁材料，进而该顶盖322先通过定位轴定位连接在该安装孔3213上，从而预先定位，接着该顶盖322磁性吸合在该磁环3215上使得该顶盖322连接在该配合槽3214内。
具体地，如图4所示，在本发明实施例中，该前壳体3211沿其两侧均向后延伸并形成有便于该机身本体10散热的通风涵道3210。该通风涵道3210的设置可以使得无人机工作时，空气从两侧的通风涵道3210穿过，一方面可以加强机身本体10的散热，另一方便还可以减少迎风面的风阻。
具体地，如图3所示，在本发明实施例中，该安装框14内还可限位连接有用于给该机身本体10供电的电池件7，该安装框14包括连接与该机身1主体上的固定架141和连接在该固定架141上的安装架142，该固定架141内设有供该储液容器6限位连接的第一安装通槽144，该安装架142内设有供该电池件7限位连接的第二安装通槽145。
在本实施例中，该固定架141和该安装架142之间还连接有隔板143，该隔板143用于将第一安装通槽144和第二安装通槽145隔开。
具体地，如图5所示，在本发明实施例中，该储液容器6包括具有储液腔体的容器主体，该容器主体包括供限位连接在该第一安装通槽144内的下箱体62和连接在该下箱体62上部并供抵接在该机身本体10上的上箱体61，该上箱体61和下箱体62优选为相互垂直，并且该上箱体61和下箱体62构成“T”型或者倒“L”型的结构。同时该上箱体61和该下箱体62连通，这样可以保证储液腔体内液体的存储量。
在本实施例中，该上箱体61上还开设有供添加液体的进液口616，该进液口616上还螺纹连接有端盖(图未示)，同时该上箱体61下部和下箱体62下部还均开设有用于喷洒液体的出液口621。
在本发明实施例中，该上箱体61包括底壁611、连接在该底壁611两侧的侧壁612和连接在两个该侧壁612顶端的顶壁613，以及连接于该底壁611前后两端的前端壁614和后端壁615，顶壁613的上端面为该第三圆弧面，该下箱体62沿该底壁611向下延伸而成。
在实际安装过程中，该下箱体62穿过该第一安装通槽144，同时该上箱体61抵接在该机身本体10上，从而完成该储液容器6的连接。
具体地，如图3所示，在本发明实施例中，该机身本体10包括供该安装壳体31连接的顶板12、与该顶板12相对设置的底板13和连接在该顶板12和该底板13之间的中转仓11，该中转仓11内连接有控制系统。
具体地，如图1至图3所示，在本发明实施例中，该机身本体10上还向外延伸有若干个机臂2，该机臂2的延伸末端还连接有动力组件5，该机身本体10底部上还连接有用于起落时缓冲的起落架4。
在本实施例中，该机身1内还连接有电调模块，该机臂2分布在机身本体10的周围，该机臂2与机身本体10固定连接。该起落架4固定于机身本体10的下方以保证无人机起飞和着陆的稳定性，动力组件5固定于机臂2远离机身本体10的端部，该动力组件5为无人机的飞行提供升力，该储液容器6搭载于机身1上且用于盛装待喷洒或者待运输的物品，电池件7固定于机身本体10 上用于向飞动力组件5提供动力，控制系统固定于机身1上，用于控制该无人机的飞行姿势。
以上所述仅为本发明的较佳实施例而已，并不用以限制本发明，凡在本发明的精神和原则之内所作的任何修改、等同替换和改进等，均应包含在本发明的保护范围之内。

Claims (10)

  1. 一种无人机，包括机身(1)、壳体组件(3)和功能组件，其特征在于：所述机身(1)包括机身本体(10)，所述壳体组件(3)连接在所述机身本体(10)的前端，所述功能组件安装于所述机身本体(10)的后端，所述功能组件的上端面为第一圆弧面，所述壳体组件(3)的上端面为第二圆弧面，所述第一圆弧面和所述第二圆弧面相邻，且所述第一圆弧面和所述第二圆弧面构成流线曲面。
  2. 如权利要求1所述的无人机，其特征在于：所述功能组件包括储液容器(6)，所述储液容器(6)安装于所述机身本体(10)的后端，所述储液容器(6)的顶部具有第三圆弧面，所述第三圆弧面邻近所述第二圆弧面，所述第一圆弧面的一部分为所述第三圆弧面。
  3. 如权利要求2所述的无人机，其特征在于：所述功能组件还包括电池件(7)，所述储液容器(6)位于所述电池件(7)和所述壳体组件(3)之间，所述电池件(7)的顶部具有第四圆弧面，所述第三圆弧面位于所述第四圆弧面和所述第二圆弧面之间，所述第一圆弧面的一部分为所述第四圆弧面。
  4. 如权利要求1至3中任一项所述的无人机，其特征在于：所述壳体组件(3)包括限位连接在所述机身本体(10)前端的安装壳体(31)和连接在所述安装壳体(31)上方的基壳体(32)，所述基壳体(32)的上端面为所述第二圆弧面。
  5. 如权利要求4所述的无人机，其特征在于：所述基壳体(32)包括连接在连接梁上的基壳本体(321)和连接在所述基壳本体(321)上的顶盖(322)，所述基壳本体(321)包括前壳体(3211)和沿所述前壳体(3211)向上且向后延伸的上壳体(3212)，所述顶盖(322)盖设在所述上壳体(3212)上，且所述顶盖(322)和所述上壳体(3212)的上端面形成所述第二圆弧面。
  6. 如权利要求5所述的无人机，其特征在于：所述上壳体(3212)上设有 供所述顶盖(322)定位连接的安装孔(3213)，所述安装孔(3213)的周沿上形成有供与所述顶盖(322)内壁抵接的配合槽(3214)，且所述顶盖(322)磁性吸合连接在所述配合槽(3214)内。
  7. 如权利要求5所述的无人机，其特征在于：所述前壳体(3211)沿其两侧均向后延伸并形成有便于所述机身本体(10)散热的通风涵道(3210)。
  8. 如权利要求3所述的无人机，其特征在于：所述储液容器(6)包括具有储液腔体的容器主体，所述容器主体包括下箱体(62)和连接在所述下箱体(62)上部的上箱体(61)，所述上箱体(61)和所述下箱体(62)连通，所述上箱体(61)的顶部为所述第三圆弧面，所述电池件(7)靠近所述上箱体(61)远离所述壳体组件(3)的一端。
  9. 如权利要求8所述的无人机，其特征在于：所述机身(1)还包括安装框(14)，所述安装框(14)包括连接于所述机身本体(10)后端的固定架(141)和连接在所述固定架(141)上的安装架(142)，所述固定架(141)内设有供所述下箱体(62)限位连接的第一安装通槽(144)，所述安装架(142)内设有供所述电池件(7)限位连接的第二安装通槽(145)。
  10. 如权利要求1至3中任一项所述的无人机，其特征在于：所述机身本体(10)上还向外延伸有若干个机臂(2)，所述机臂(2)的延伸末端还设置有动力组件(5)，所述机身本体(10)的底部上还设置有用于起落时缓冲的起落架(4)。
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AU2018310402B2 (en) 2021-06-10
KR20200003405A (ko) 2020-01-09
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EP3663189A1 (en) 2020-06-10
US20200156789A1 (en) 2020-05-21

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