WO2019134399A1 - 无人机及其机壳 - Google Patents

无人机及其机壳 Download PDF

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Publication number
WO2019134399A1
WO2019134399A1 PCT/CN2018/106253 CN2018106253W WO2019134399A1 WO 2019134399 A1 WO2019134399 A1 WO 2019134399A1 CN 2018106253 W CN2018106253 W CN 2018106253W WO 2019134399 A1 WO2019134399 A1 WO 2019134399A1
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WO
WIPO (PCT)
Prior art keywords
casing
side wall
arm
lower cover
drone
Prior art date
Application number
PCT/CN2018/106253
Other languages
English (en)
French (fr)
Inventor
张雅文
张彬
Original Assignee
深圳市大疆创新科技有限公司
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 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN201880014411.2A priority Critical patent/CN110352162A/zh
Publication of WO2019134399A1 publication Critical patent/WO2019134399A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling
    • B64U20/96—Cooling using air
    • 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
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/291—Detachable rotors or rotor supports

Definitions

  • the embodiment of the invention relates to a drone and a casing thereof, and belongs to the technical field of unmanned aerial vehicles.
  • the drone is a non-manned aerial vehicle that is operated using radio remote control equipment and self-contained program control devices.
  • UAVs can generally be divided into: unmanned fixed-wing aircraft, unmanned vertical take-off and landing aircraft, unmanned airships, unmanned helicopters, unmanned multi-rotor aircraft, unmanned paraplanes, and so on.
  • Embodiments of the present invention provide a drone and a casing thereof to solve the above or other potential problems existing in the prior art.
  • a casing of a drone is provided, the casing is provided with a heating element of the drone, and the casing is provided with an air inlet duct, and the air inlet duct
  • the paddle wind generated when the propeller rotates is introduced into the casing; the bottom of the casing is provided with an air outlet, and the air outlet is used for the paddle after heat transfer with the heating element
  • the wind is led out of the casing; wherein the air outlet is provided as at least one through hole for mating with a heat sink of the heat generating component.
  • the casing as described above comprising: a side wall, an upper cover covering the upper end opening of the side wall, and a lower cover covering the lower end opening of the side wall;
  • the through hole formed in the lower cover includes at least one of a strip hole, a square hole, a round hole, and a window.
  • the inlet air duct comprises: a through groove formed in the side wall, and a deflector disposed on the side wall or the lower cover; the diversion The plate extends from the through slot obliquely upward away from the housing.
  • the inlet air duct comprises: a through groove formed in the lower cover, and a deflector disposed on the lower cover; the deflector is from the through The slot extends obliquely upward away from the housing.
  • the inlet air duct includes: a through groove opened in the upper cover, and a deflector provided on the upper cover, the side wall or the lower cover
  • the baffle extends from the through slot to an obliquely upward direction away from the casing.
  • a drone comprising: the casing, a heat generating component mounted in the casing, a propeller, and an arm connecting the casing and the propeller.
  • the arm includes: a first arm and a second arm, and an angle between the first arm and the second arm; the first arm The first end of the first arm and the second end of the second arm are coupled to the propeller, and the second end of the first arm and the second end of the second arm are respectively coupled to the casing.
  • the air inlet duct is disposed on the side wall of the casing of the drone, and the air outlet is opened at the bottom of the casing, and flows upward from the rotation plane formed by the rotation of the blade of the propeller
  • the air below enters the accommodating cavity of the casing through the air inlet duct, and then transfers heat to the electronic components installed in the casing, and finally flows out of the accommodating cavity from the air outlet at the bottom of the casing, thereby reducing the temperature of the electronic component, thereby
  • the temperature of the electronic component can be maintained within the normal operating temperature, and then the electronic component can operate normally and stably.
  • FIG. 1 is a schematic structural diagram of a drone according to an embodiment of the present invention.
  • Figure 2 is an exploded view of the drone of Figure 1;
  • Figure 3 is a cross-sectional view of the drone of Figure 1;
  • Figure 4 is a plan view of the heat sink of Figure 1;
  • Figure 5 is a left side view of the heat sink of Figure 1;
  • Figure 6 is a bottom plan view of the heat sink of Figure 1;
  • Figure 7 is a plan view of the lower cover of Figure 1;
  • Figure 8 is a left side view of the lower cover of Figure 1;
  • Figure 9 is a bottom plan view of the lower cover of Figure 1;
  • 12a front side wall
  • 12b rear side wall
  • 12c left side wall
  • FIG. 1 is a schematic structural view of a drone provided in the present embodiment
  • FIG. 2 is an exploded view of the unmanned aerial vehicle of FIG. 1
  • FIG. 3 is a cross-sectional view of the unmanned aerial vehicle of FIG.
  • the drone of this embodiment includes: a fuselage, an arm 2, a power component, and a stand.
  • the structure of the drone according to the order of the power component, the arm 2, the fuselage, and the tripod.
  • the power assembly includes a propeller 3, a motor (not shown), and an ESC (not shown).
  • the propeller 3 is rotated by the motor to provide power for the drone's ascending, advancing, rotating, and the like.
  • the propeller 3 has a blade and a hub.
  • the hub is fixed to the output shaft of the motor, and the blade is mounted on the hub.
  • the output shaft of the motor drives the hub to rotate, the blade mounted on the hub also rotates to form The plane is rotated to direct the air around the propeller 3 below the plane of rotation, i.e., to form a downward paddle to provide lift to the drone.
  • Electrically invoked to control motor operation which is electrically coupled to a flight control circuit board as will be described below to control motor start/stop, speed, steering, etc. based on control signals from the flight control circuit board to control the flight direction of the drone And flight speed.
  • the plurality of propellers 3 may be distributed in a radial form around the fuselage, that is, a plurality of propellers 3 are spaced apart from the outer edge of the casing 1 of the fuselage.
  • the quadrotor drone shown in Figures 1 to 3 includes four propellers 3 that are symmetrically disposed about the transverse and longitudinal axes of the drone.
  • a protective cover 4 for protecting the propeller 3 may be disposed.
  • the protective cover 4 may be connected to the arm by, for example, a snapping manner, specifically, being connected to the arm 2 away from the machine.
  • One end of the body and a fan-shaped structure extending away from the ground One end of the body and a fan-shaped structure extending away from the ground.
  • the protective cover 4 can also be fixedly connected to other components of the casing 1 and extend away from the ground, and the structure of the protective cover 4 is not limited to a sector structure.
  • the arm 2 is used to connect the propeller 3 and the fuselage.
  • the arm 2 may be a single hollow rod made of metal, plastic, or carbon fiber material. Of course, in other embodiments, the arm 2 may also be a plate structure or a solid rod.
  • the propeller 3 is fixed to one end of the arm 2 away from the body, and the other end of the arm 2 is fixed to the casing 1 of the body to be described later.
  • the propeller 3 is detachably or rotatably mounted on the end of the arm 2 away from the fuselage to facilitate storage and transportation of the drone.
  • the other end of the arm 2 can also be detachably or rotatably connected to the casing 1 of the fuselage, thereby improving the convenience of storage or transportation of the drone.
  • the arm 2 may have a linear shape or a polygonal shape.
  • the arm 2 of FIGS. 1 to 3 includes a first arm 21 and a second arm 22, the two arms having an angle between them and forming a triangular structure with the body, thereby improving the absence of The stability of man and machine. 1 and 2, the first end of the first arm 21 and the first end of the second arm 22 are fixed, and the propeller 3 is fixed at the connection position of the two; the second end of the first arm 21 and The second ends of the second arms 22 are respectively fixed to the casing 1 of the fuselage described below.
  • the first arm 21 and the second arm 22 extend from different connection positions of the two to be fixed to the casing 1 of the body to form a triangular arm 2 structure.
  • a weight reducing slot 23 is defined on the first arm 21 and the second arm 22 to reduce the weight of the drone, thereby improving the flying height and the endurance time of the drone.
  • the drone when it is a multi-rotor drone, it includes a plurality of arms 2, which are dispersedly disposed around the fuselage of the drone, and Radially extending outward.
  • the number of power components is the same as the number of the arms 2, and each of the propellers 3 is mounted at one end of one of the arms 2 away from the body.
  • a mounting hole can be opened at one end of the arm 2 away from the body, and Set the motor mount in the mounting hole.
  • the motor of the power assembly is fixed in the mount, and the hub of the propeller 3 is fixed on the output shaft of the motor.
  • the ESC can be integrated with the motor, or the ESC can be mounted in the cavity of the arm 2.
  • the body is a main part of the drone, and includes a casing 1, and a heat generating element 5 placed inside the casing 1.
  • the heating element 5 disposed in the casing 1 may be any type, any type of electronic component or integrated module that the UAV is installed in the casing 1 for functions such as flight, shooting, positioning navigation, and the like.
  • the casing 1 may be equipped with a flight control circuit board, a GPS positioning module, a Beidou positioning module, a gyroscope, a wireless receiving module, an image transceiver module electrically connected to a camera on the pan/tilt head, and the like.
  • the heat output of today's drones is much higher than that of the previously produced or developed drones.
  • the present embodiment provides an improved cabinet 1 in which an air inlet duct 8 is provided on the cabinet 1 to rotate the propeller shaft 3 in the power unit to be described later.
  • the air outlet is at least one through hole 131 disposed at the bottom of the casing 1, and the at least one through hole 131 cooperates with the heat sink 7 of the heat generating component 5 to be described later.
  • the drone since the drone generally flies in a high air, the temperature of the air around it is relatively low. Therefore, after the low-temperature air is introduced into the casing 1, the heat-dissipating effect on the heat-generating component 5 can be improved. And will not increase the noise of the drone.
  • the casing 1 is generally made into a circle, an ellipse, a rectangle, or other geometric shapes. It should be understood by those skilled in the art that the inlet air duct 8 introduced below may be disposed on the casing 1 of any shape, but for the sake of brevity, the rounded rectangular machine shown in FIGS. 1 to 3 will be described below.
  • the case 1 is taken as an example, and the casing 1 and its inlet air duct 8 and the air outlet provided at the bottom of the casing 1 will be described.
  • the corresponding air inlet duct 8 and the air outlet can be disposed on the casing 1 of other shapes by direct or simple transformation, so as to heat the internal heating component of the casing 1.
  • the heat dissipation of 5, the direct or simple conversion of the drone and its casing 1 still fall within the scope of the present invention.
  • the cabinet 1 includes an upper cover 11, a side wall 12, and a lower cover 13.
  • the side wall 12 has an upper end opening and a lower end opening, the upper cover 11 covers the upper end opening, and the lower cover 13 covers the lower end opening, so that the upper cover 11, the side wall 12 and the lower cover 13 are combined to accommodate the above The accommodating cavity of the heating element 5.
  • the side wall 12 includes a front side wall 12a at the front end, a rear side wall 12b disposed opposite the front side wall 12a, and a left side fixed to the left side of the front side wall 12a and the rear side wall 12b.
  • the side wall 12c and the right side wall 12d fixed to the right side of the front side wall 12a and the rear side wall 12b.
  • An intake air duct 8 is disposed at each of the front ends of the left side wall 12c and the right side wall 12d.
  • the left side air inlet duct 8 is inclined to the left side wall 12c
  • the right side air inlet duct 8 is inclined to the right side wall 12d.
  • left inlet air duct 8 and the right side air inlet duct 8 extend obliquely upward from the casing 1, so that the air inlets of the left inlet air duct 8 and the right inlet air duct 8 are oriented.
  • the air inlet of the inlet air duct 8 should be lower than the height of the rotation plane formed by the rotation of the propeller 3. This also conforms to the existing design concept that the height of the propeller 3 of the drone is generally set higher than the upper cover 11 of the casing 1. Of course, if the propeller 3 is disposed lower than the height of the upper cover 11, the blade air of the propeller 3 can be introduced into the casing 1 only by slightly adjusting the position of the inlet air duct 8.
  • the air inlet of the left inlet air duct 8 is lower than the height of the upper left propeller 3 (hereinafter referred to as the first propeller), specifically, the rotation of the blade lower than that of the first propeller 3.
  • the rotation plane of the right inlet air duct 8 is lower than the height of the right upper propeller 3 (hereinafter referred to as the second propeller), specifically, a rotation plane formed by the rotation of the blade of the second propeller 3 .
  • only the left inlet air duct 8 or the right side air inlet duct 8 may be provided on the casing 1.
  • the right inlet air duct 8 may be disposed at the rear end of the right side wall 12d, that is, the right side air passage is disposed at a position near the lower right propeller (hereinafter referred to as a third propeller), or the left side is advanced.
  • the wind tunnel 8 is disposed at the rear end of the left side wall 12c, that is, the left inlet air duct 8 is disposed at a position close to the lower left propeller (hereinafter referred to as the fourth propeller).
  • any number of inlet air ducts 8 may be provided on the left side wall 12c and the right side wall 12d while ensuring the strength of the cabinet 1.
  • the plurality of inlet air ducts 8 may be symmetrical with respect to the longitudinal axis or the transverse axis of the body, or both The longitudinal axis and the transverse axis of the fuselage are symmetrical.
  • FIG. 3 shows that the front end of the left side wall 12c of the cabinet 1 and the front end of the right side wall 12d are each provided with an inlet air duct 8 (left side air duct 8 and right side air duct). 8)
  • the two inlet ducts 8 are symmetrical about the longitudinal axis of the fuselage.
  • the propeller 3 disposed around the fuselage rotates, and the air flowing below the plane of rotation formed by the rotation of the blade enters the accommodating cavity of the casing 1 from the inlet air duct 8 and exchanges heat with the heat generating component 5.
  • one or more air outlets opened from the lower cover 13 flow out of the air body, so that the heat generated by the heat generating component 5 is taken out of the air body, so that the temperature inside the casing 1 is lowered, and the heating element 5 can be normally and stably operated. .
  • the casing 1 of the present embodiment is provided with a right through slot 81 at the bottom of the right side wall 12d.
  • the right through slot 81 has a notch toward the lower cover 13, and the right side of the lower cover 13 is to the upper right.
  • the right baffle 82 is formed to extend, and in other words, the right side of the lower cover 13 extends to the right upper second propeller 3 to form a right baffle 82.
  • the right deflector 82 and the right through slot 81 having a notch surround the right inlet air duct 8.
  • the right through slot 81 may not be disposed at the bottom of the right side wall 12d, but may be disposed at an intermediate portion between the top and bottom of the right side wall 12d.
  • the through slot 81 does not have a notch, that is, the top end, the bottom end, the front end and the rear end of the right through slot 81 are closed, and the right deflector 82 is formed on the right side wall 12d or the lower cover 13, specifically The right baffle 82 is formed to extend from the bottom surface of the right through slot 81 or the right side of the lower cover 13 to the upper right.
  • the right through slot 81 may also be disposed on the lower cover 13, and the right deflector 82 is also disposed on the lower cover 13.
  • a right through groove 81 may be formed on the right side of the lower cover 13, and a right deflector 82 extending to the upper right may be provided on the lower cover 13.
  • the right through slot 81 may be disposed on the upper cover 11, and the right deflector 82 may be disposed on the upper cover 11, the side wall 12, or the lower cover 13.
  • a right through groove 81 is formed on the right side of the upper cover 11, and a baffle 82 extending obliquely upward is provided on the upper cover 11.
  • the right baffle 82 may be integrally formed with the upper cover 11, the side wall 12, or the lower cover 13; alternatively, the right baffle 82 may be a separate component, which is conventional.
  • the fixing method (for example, bonding, bolting, or snapping) is fixed to the upper cover 11, the side wall 12, or the lower cover 13.
  • the shape of the right deflector 82 toward the inner surface of the right through groove 81 may be arbitrary.
  • the inner surface of the right baffle 82 includes a first plane and a second plane that are joined together. An obtuse angle is formed between the first plane and the second plane, so that the right inlet air duct 8 has a large air inlet area, and the intake air volume is increased to improve heat dissipation efficiency. A smooth transition between the first plane and the second plane can also be achieved to reduce the wind resistance of the air flowing through the inlet duct 8, thereby reducing the impact on the flight efficiency of the drone.
  • the inner surface of the right baffle 82 is a curved surface to further reduce the wind resistance of the air flowing through the inlet air duct 8, thereby improving the air intake efficiency and reducing the impact on the flight efficiency of the drone.
  • the orthographic projection of the right intake air duct 8 on the plane of rotation formed by the blades of the second propeller 3 is located in the plane of rotation.
  • the distance that the right through slot 81 extends along the length direction of the right side wall 12d can be set according to the actual heat dissipation efficiency, the structural strength of the casing 1, and the influence on the flight efficiency. limited.
  • the structure of the left intake air duct 8 is the same as that of the right intake air duct 8.
  • the structures of the left inlet air duct 8 and the right inlet air duct 8 may also have a slight change, for example, the left through slot 81 and the left diversion of the left inlet air duct 8
  • the plates 82 are both disposed at the intermediate portion of the top end and the bottom end of the left side wall 12c, the right through groove 81 of the right inlet air duct 8 is disposed at the bottom of the right side wall 12d, and the right deflector 82 is formed at the right side of the lower cover 13.
  • the upper cover 11, the side wall 12, and the lower cover 13 described in the above embodiments are separate three components, the upper cover 11 and the side wall 12 may be integrally formed into a single piece, or The lower cover 13 and the side wall 12 are integrally formed into a single piece, and there is no need to substantially change the structure of the inlet air duct 8.
  • a heat sink 7 is further disposed between the heat generating element 5 and the lower cover 13, and the heat sink 7 is fixed to the bottom of the heat generating element 5 by a heat conductive glue or the like.
  • FIG. 4 is a top view of the heat sink 7 of FIG. 1;
  • FIG. 5 is a left side view of the heat sink 7 of FIG. 1;
  • FIG. 6 is a bottom view of the heat sink 7 of FIG.
  • the heat sink 7 may be a plate-like structure made of metal, which is bonded to the lower portion of the heat generating component 5 by a thermal conductive adhesive, and heat generated by the heat generating component 5 is transmitted to the heat sink through the thermal conductive adhesive. 7 on.
  • the drone is started, the propeller 3 rotates, and the air flows downward from above the plane formed by the rotation of the blades of the propeller 3 to form a paddle wind, and enters the accommodating cavity of the casing 1 through the inlet air duct 8 Then, it is blown from the bottom surface of the heat sink 7 to exchange heat with the heat sink 7, and finally flows out of the casing 1 from the air inlet opened in the lower cover 13 to bring the heat of the heat generating component 5 to the outside of the casing 1.
  • one or more heat dissipating fins 71 are formed at the bottom of the heat sink 7 to increase the bottom surface area of the heat sink 7, thereby improving heat dissipation efficiency.
  • the heat sink 7 is further provided with a second bolt hole 72, so that the heat sink 7 can be fixed by bolts to the casing 1 or the heating element 5 (for example, a flight control circuit board), thereby improving the connection of the heat sink 7. strength.
  • electromagnetic interference is generated to the other heating elements 5 of the drone (for example, the electric adjustment of the power component or the motor of the motor, the pan/tilt head, and the camera mounted on the pan/tilt).
  • An electromagnetic shielding plate 6 is also disposed between the heating element 5.
  • Figure 7 is a plan view of the lower cover 13 of Figure 1;
  • Figure 8 is a left side view of the lower cover 13 of Figure 1
  • Figure 9 is a bottom plan view of the lower cover 13 of Figure 1.
  • the lower cover 13 defines a plurality of elongated holes along the longitudinal direction of the heat sink 7 as ventilation holes 131 , and the plurality of elongated holes are arranged in parallel to improve the air blowing effect, and then improve. Cooling efficiency.
  • the plurality of elongated holes may extend in the direction of the heat sink 7 to match the structure of the heat dissipating fins 71 at the bottom of the heat sink 7, so that the heat dissipating fins 71 may be exposed through the elongated holes and directly contact with the outside cold air. , thereby improving heat dissipation efficiency.
  • venting holes 131 may also be one of a square hole, a circular hole, and a window opening, and the shape, size, density, and the vent hole 131 are designed.
  • the arrangement can be variously designed, and the heat sink 7 can be used to dissipate heat from the heat generating component 5, which is not specifically limited herein.
  • a plurality of first bolt holes 132 are defined in the lower cover 13 , and the lower cover 13 is fixed on the heating element 5 in the receiving cavity by bolts, for example, the lower cover 13 is further fixed to the flight control circuit board, so as to improve The stability of the flight control board is protected from sloshing.
  • the tripod is used to support the crop on the ground or on the ground when the drone is landed, so as to prevent the casing 1 from contacting the ground or the ground to protect the chassis 1 or the platform installed at the bottom of the casing 1.
  • the tripod may be fixed to the lower cover 13 of the casing 1, or may be disposed under the arm 2, or may be a lower cover 13 of the casing 1 and a lower leg of the arm 2, and the stand is provided. It may be a buffer structure such as a soft rubber material.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Cooling Or The Like Of Electrical Apparatus (AREA)

Abstract

一种无人机及机壳（1），机壳（1）内置有无人机的发热元件（5），机壳（1）上设置有进风风道（8），进风风道（8）用于将螺旋桨（3）旋转时产生的桨风导入机壳（1）内；机壳（1）的底部设有出风口，出风口用于将与发热元件（5）进行热传递后的桨风导出机壳（1）；其中，出风口被设置为用于与发热元件（5）的散热器（7）相配合的至少一个通孔（131）。该技术方案通过在机壳（1）上设置进风风道（8），并在机壳（1）的底部设置出风口，从而可以将螺旋桨（3）旋转时产生的桨风导入到机壳（1）内，继而与机壳（1）内的发热元件（5）进行热交换后从出风口流出机壳（1），进而实现为发热元件（5）散热降温的作用。

Description

无人机及其机壳 技术领域
本发明实施例涉及一种无人机及其机壳，属于无人飞行器技术领域。
背景技术
无人驾驶飞机简称“无人机”(“UAV”)，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行器。无人机一般可以分为：无人固定翼飞机、无人垂直起降飞机、无人飞艇、无人直升机、无人多旋翼飞行器、无人伞翼机等。
随着无人机的畅销，消费者对于无人机功能的需求越来越多，为了给客户带来更好的体验，现在的无人机相比于几年前、甚至相比于几个月前生产的无人机而言，都会增加很多提高用户体验、和/或、提高飞行安全性的功能。为了实现这些功能，不可避免的会在机身内部使用更多的电子元件、或者增加电子元件的功耗，来满足新功能的需求。
但是，增加电子元件或者增大电子元件的功耗虽然能够增加无人机的功能、和/或、提高无人机的安全性，但是也不可避免地会使机身内部产生更多的热量，如果不能及时将这些热量消除，就极有可能会导致无人机发生故障。
发明内容
本发明实施例提供一种无人机及其机壳，以解决现有技术存在的以上或者其他潜在问题。
根据本发明的实施例，提供一种无人机的机壳，所述机壳内置有所述无人机的发热元件，所述机壳上设置有进风风道，所述进风风道用于将所述螺旋桨旋转时产生的桨风导入所述机壳内；所述机壳的底部设有出风口，所述出风口用于将与所述发热元件进行热传递后的所述桨风导出所述机壳；其中，所述出风口被设置为用于与所述发热元件的散热器相配合的至少一个通孔。
如上所述的机壳，包括：侧壁、盖合在侧壁的上端开口处的上盖、以及盖合在侧壁的下端开口处的下盖；
所述下盖上开设的所述通孔包括条形孔、方形孔、圆孔、开窗中的至少一种。
如上所述的机壳，其中，所述条形孔沿所述散热器的长度方向延伸。
如上所述的机壳，其中，所述进风风道包括：在所述侧壁上开设的通槽，以及设置在所述侧壁或者所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
如上所述的机壳，其中，所述进风风道包括：在所述下盖上开设的通槽，以及设置在所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
如上所述的机壳，其中，所述进风风道包括：在所述上盖上开设的通槽，以及设置在所述上盖、所述侧壁或者所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
如上所述的机壳，其中，所述导流板朝向所述通槽的内表面为弧面。
如上所述的机壳，其中，所述上盖和所述侧壁为一体成型的一体件，或者，所述下盖和所述侧壁为一体成型的一体件。
如上所述的机壳，其中，所述螺旋桨旋转形成有旋转平面，所述进风风道在所述旋转平面上的正投影位于该旋转平面内。
如上所述的机壳，其中，所述进风风道设置在靠近所述机壳的前端的位置。
根据本发明的实施例，提供一种无人机，包括：上述机壳、安装在所述机壳内的发热元件、螺旋桨、以及连接所述机壳与所述螺旋桨的机臂。
如上所述的无人机，其中，所述发热元件和所述机壳的底部之间还设置有散热器，所述散热器固定在所述电子元件的底部。
如上所述的无人机，其中，所述散热器的底部设置有多个散热鳍。
如上所述的无人机，其中，所述机臂包括：第一支臂和第二支臂，且所述第一支臂和第二支臂之间具有夹角；所述第一支臂的第一端和所述第二支臂的第一端与所述螺旋桨连接，所述第一支臂的第二端和所述第二支臂的第二端分别与所述机壳连接。
如上所述的无人机，其中，所述第一支臂和第二支臂上开设有减重槽。
如上所述的无人机，其中，所述机壳的进风风道位于所述第一支臂和第二支臂之间。
根据本实施例的技术方案，在无人机的机壳的侧壁上设置进风风道、并在机壳的底部开设有出风口，从螺旋桨的桨叶旋转所形成的旋转平面的上方流向下方的空气经该进风风道进入机壳的容纳腔内，然后与机壳内安装的电子元件进行热传递，最后从机壳底部的出风口流出容纳腔，从而降低电子元件的温度，使得电子元件的温度能够维持在正常工作的温度以内，继而电子元件能够正常稳定的工作。
本发明的附加方面的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
通过参照附图的以下详细描述，本发明实施例的上述和其他目的、特征和优点将变得更容易理解。在附图中，将以示例以及非限制性的方式对本发明的多个实施例进行说明，其中：
图1为本发明实施例提供的无人机的结构示意图；
图2为图1中无人机的爆炸图；
图3为图1中无人机的剖视图；
图4为图1中散热器的俯视图；
图5为图1中散热器的左视图；
图6为图1中散热器的仰视图；
图7为图1中下盖的俯视图；
图8为图1中下盖的左视图；
图9为图1中下盖的仰视图；
图中：
1、机壳；          11、上盖；          12、侧壁；
12a、前侧壁；      12b、后侧壁；       12c、左侧壁；
12d、右侧壁；      13、下盖；          131、通孔；
132、第一螺栓孔；     2、机臂；        21、第一支臂；
22、第二支臂；   23、减重槽；    3、螺旋桨；
4、保护罩；      5、发热元件；   6、电磁屏蔽板；
7、散热器；      71、散热鳍；    72、第二螺栓孔；
8、进风风道；    81、通槽；      82、导流板。
具体实施方式
下面详细描述本发明的实施例，所述实施例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例是示例性的，旨在用于解释本发明，而不能理解为对本发明的限制。
图1为本实施例提供的无人机的结构示意图，图2为图1中无人机的爆炸图；图3为图1中无人机的剖视图。如图1至图3所示，本实施例的无人机包括：机身、机臂2、动力组件、以及脚架。为了使本领域技术人员更好的了解本实施例的技术方案及其优点，以下按照动力组件、机臂2、机身、以及脚架的顺序对无人机的结构进行介绍。
参照图1至图3，动力组件包括有：螺旋桨3、电机(图中未示出)、以及电调(图中未示出)。螺旋桨3由电机带动旋转，从而为无人机的上升、前进、转动等提供动力。螺旋桨3具有桨叶和桨毂，桨毂与电机的输出轴固定，桨叶安装在桨毂上，当电机的输出轴带动桨毂旋转时，安装在桨毂上的桨叶也跟随转动以形成旋转平面，从而将螺旋桨3周围的空气引到旋转平面的下方，也即形成向下的桨风，以便为无人机提供升力。电调用来控制电机工作，其与下文将要描述到的飞行控制电路板电连接，以根据飞行控制电路板发出的控制信号控制电机启动/停止、转速、转向等，进而控制无人机的飞行方向和飞行速度。
进一步，螺旋桨3可以有多个，从而形成如图1至图3所示的多旋翼无人机。具体的，这多个螺旋桨3以放射状的形式分散布置在机身的四周，也即多个螺旋桨3间隔设置在机身的机壳1的外边缘。例如，图1至图3示出的四旋翼无人机包括有四个螺旋桨3，这四个螺旋桨3关于无人机的横轴线和纵轴线对称设置。
可选地，参照图1至图3，本实施例中可以设有用于保护螺旋桨3的 保护罩4，保护罩4可以通过诸如卡接方式与机臂连接，具体为连接在机臂2远离机身的一端、并往远离地面方向延伸的扇形结构。可以理解，在其他一些实施方式中，保护罩4也可以与机壳1的其它部件固定连接、并往远离地面方向延伸，并且保护罩4的结构也不限定为扇形结构。
机臂2用来连接螺旋桨3和机身。具体的，机臂2可以是由金属、塑料、或者碳纤维材料制作成的单根中空的杆件，当然，在另外一些实施方式中，机臂2也可以是板状结构或者是实心的杆件。螺旋桨3固定在机臂2远离机身的一端，机臂2的另一端则与下文将要描述到的机身的机壳1固定。可选的，螺旋桨3可拆卸、或者可转动的安装在机臂2远离机身的一端，以方便无人机的储藏与运输。同理的，机臂2的另一端也同样可以可拆卸、或者可转动的与机身的机壳1连接，从而提高无人机的储藏或者运输中的便捷性。
具体来说，机臂2可以为直线形状，或者也可以是多边形形状。例如，图1至图3的机臂2包括第一支臂21和第二支臂22，这两个支臂之间具有夹角、并且与机身之间形成了三角形结构，从而提高了无人机的稳定性。继续参阅图1和图2，第一支臂21的第一端和第二支臂22的第一端固定，螺旋桨3固定在这两者的连接位置；第一支臂21的第二端和第二支臂22的第二端分别与下文描述的机身的机壳1固定。换句话来说，第一支臂21和第二支臂22从二者的连接位置往不同的方向延伸以与机身的机壳1固定，从而形成三角形的机臂2结构。可选地，在第一支臂21和第二支臂22上开设有减重槽23，以减轻无人机的重量，从而提高无人机的飞行高度和续航时间。
此外，从图1至图3可以看出，当无人机为多旋翼无人机时，其包括有多个机臂2，这些机臂2分散设置在无人机的机身的四周，并呈放射状往外延伸。动力组件的个数与机臂2的个数相同，每个螺旋桨3均安装在其中一个机臂2远离机身的一端，例如，可以在机臂2远离机身的一端开设安装孔、并在安装孔内设置电机安装座。动力组件的电机固定在安装座内，螺旋桨3的桨毂固定在电机的输出轴上。电调可以与电机集成在一起，或者电调可以安装在机臂2的空腔中。
机身是无人机的主体部分，其包括：机壳1、以及置于机壳1内的发 热元件5。具体来说，置于机壳1内的发热元件5可以是无人机为了实现飞行、拍摄、定位导航等功能所安装到机壳1内的任意型号、任意类型的电子元器件或者集成模块。举例来说，机壳1内可以安装有飞行控制电路板、GPS定位模块、北斗定位模块、陀螺仪、无线接收模块、与云台上的摄像头电连接的图像收发模块等等。
由于安装或者集成到机壳1内的电子元器件或者集成模块的数量越来越多，现在的无人机的发热量相较于之前生产或者开发出来的无人机的发热量增大了很多。为了使无人机能够正常工作，必然需要使发热元件5散发的这些热量尽快散失到机壳1外，以便将机壳1内的温度降到发热元件5能够正常工作的温度范围以内。基于此，本实施例提供了一种经过改进的机壳1，其在机壳1上设置有进风风道8，以将下文将要描述到的动力组件中的螺旋桨3旋转所产生的桨风引入到机壳1内，从而使这些桨风与发热元件5进行热传递，然后这些桨风再被机壳1的底部所设置的出风口导出机壳1，以起到降低机壳1内温度的目的。其中，出风口为配置在机壳1底部的至少一个通孔131，这至少一个通孔131与下文将要描述到的发热元件5的散热器7相配合。
此外，由于无人机一般在较高的空中飞行，其周围的空气的温度都比较低，因此，将这些低温的空气导入到机壳1内后，还可以提高对发热元件5的散热降温效果，并且还不会增加无人机的噪声。
机壳1，一般制作成为圆形、椭圆形、矩形、或者其他几何形状。本领域技术人员应该理解，下面介绍到的进风风道8可以设置在任意形状的机壳1上，但是为了描述更加简洁，下面将以图1至图3中的示出的圆角矩形机壳1为例，对机壳1及其进风风道8、以及设置在机壳1底部的出风口进行说明。本领域技术人员应该理解，在下述实施例的基础上，可以通过直接或简单变换后在其他形状的机壳1上设置相应的进风风道8以及出风口，以便对机壳1内部发热元件5的散热降温，这些直接或者经过简单变换的无人机及其机壳1依然属于本发明的保护范围。
继续参照图1至图3，机壳1包括：上盖11、侧壁12、和下盖13。侧壁12具有上端开口和下端开口，上盖11盖合在上端开口处，下盖13盖合在下端开口处，从而上盖11、侧壁12和下盖13围合成一个用于容置 上述发热元件5的容纳腔。
请看图1，具体来说，侧壁12包括位于前端的前侧壁12a、与前侧壁12a相对设置的后侧壁12b、与前侧壁12a和后侧壁12b的左侧固定的左侧壁12c、以及与前侧壁12a和后侧壁12b的右侧固定的右侧壁12d。在左侧壁12c和右侧壁12d的前端各设置有一个进风风道8，左侧进风风道8倾斜于左侧壁12c、右侧进风风道8倾斜于右侧壁12d，且左侧进风风道8和右侧进风风道8往远离所述机壳1的斜上方延伸，从而使左侧进风风道8和右侧进风风道8的进风口均朝向螺旋桨3所产生的桨风的流动方向，以便将桨风导入到机壳1内。
可以理解的，由于进风风道8需要将螺旋桨3旋转所产生的桨风导入到机壳1内，因此，进风风道8的进风口应该低于螺旋桨3旋转所形成的旋转平面的高度，这也符合无人机的螺旋桨3的高度一般都设置为高于机壳1上盖11的现有设计理念。当然，如果螺旋桨3设置的低于上盖11的高度，此时只需要稍微调整进风风道8的位置即可实现将螺旋桨3的桨风导入机壳1内的目的。
对于图3而言，其左侧进风风道8的进风口低于左上方螺旋桨3(下称第一螺旋桨)的高度，具体来说，是低于第一螺旋桨3的桨叶旋转所形成的旋转平面；右侧进风风道8的进风口低于右上方螺旋桨3(下称第二螺旋桨)的高度，具体来说，是低于第二螺旋桨3的桨叶旋转所形成的旋转平面。
可选地，在机壳1上也可以只设置左侧进风风道8或者右侧进风风道8。
又可选地，右侧进风风道8可以设置在右侧壁12d的后端，也即将右侧风道设置在靠近右下方螺旋桨(下称第三螺旋桨)的位置，或者将左侧进风风道8设置在左侧壁12c的后端，也即将左侧进风风道8设置在靠近左下方螺旋桨(下称第四螺旋桨)的位置。
还可选地，在保证机壳1强度的情况下，可以在左侧壁12c、右侧壁12d上设置任意数量的进风风道8。
此外，当机壳1的左侧壁12c和右侧壁12d上设置有多个进风风道8时这多个进风风道8可以相对于机身的纵轴线或者横轴线对称，或者同时 关于机身的纵轴线和横轴线对称。例如，图3中示出了在机壳1的左侧壁12c的前端以及右侧壁12d的前端各设置有一个进风风道8(左侧进风风道8和右侧进风风道8)，这两个进风风道8关于机身的纵轴线对称。
当无人机起飞以后，分散设置在机身周围的螺旋桨3旋转，流向桨叶旋转形成的旋转平面下方的空气从进风风道8进入机壳1的容纳腔内，与发热元件5换热后从下盖13所开设的一个或者多个出风口流出机身，从而将发热元件5发出的热量带出机身，以便使机壳1内的温度降低，保证发热元件5能够正常稳定的工作。
继续参考图3，本实施例的机壳1在右侧壁12d的底部开设有右通槽81，该右通槽81具有朝向下盖13方向的缺口，下盖13的右侧边往右上方延伸形成有右导流板82，换句话说，下盖13的右侧边往位于右上方的第二螺旋桨3方向延伸形成有右导流板82。该右导流板82和具有缺口的右通槽81围合成右侧进风风道8。
可以理解的是，在另外一些实施方式中，右通槽81也可以不设置在右侧壁12d的底部，而是设置在右侧壁12d的顶部和底部之间的中间部分，此时，右通槽81不具有缺口，也即，右通槽81的顶端、底端、前端和后端均是封闭的，右导流板82则形成在右侧壁12d或者下盖13上，具体为从右通槽81的底面、或者下盖13的右侧边往右上方延伸形成该右导流板82。
在其他一些实施方式中，右通槽81还可以设置在下盖13上，此时也将右导流板82设置在下盖13上。例如，可以在下盖13的右侧边开设右通槽81，并且在下盖13上设置往右上方延伸的右导流板82。或者，右通槽81还可以设置在上盖11上，此时右导流板82可以设置在上盖11、侧壁12或者下盖13上。例如，在上盖11的右侧边开设右通槽81，并在上盖11上设置往斜向上方延伸的导流板82。
在本实施例中，右导流板82可以与上盖11、侧壁12、或者下盖13为一体成型的一体件；或者，该右导流板82可以为单独的部件，其通过常规的固定方式(例如粘接、螺栓连接、或者卡接等方式)与上盖11、侧壁12、或者下盖13的固定。
进一步，右导流板82朝向右通槽81的内表面的形状可以是任意的。 例如，右导流板82的内表面包括连接在一起的第一平面和第二平面。第一平面和第二平面之间形成钝角，从而使右侧进风风道8具有较大的进风面积，提高进风风量以提高散热效率。第一平面和第二平面之间还可以圆滑过渡，以降低空气流经进风风道8时的风阻，从而减小对无人机飞行效率的影响。又如，右导流板82的内表面为弧面，以进一步降低空气流经进风风道8的风阻，从而提高进风效率、以及降低对于无人机飞行效率的影响。
可选地，为了提高提高右侧进风风道8的进风能力，右侧进风风道8在第二螺旋桨3的桨叶所形成的旋转平面上的正投影位于该旋转平面内。
需要说明的是，右通槽81沿着右侧壁12d的长度方向延伸的距离可以根据实际需要的散热效率、机壳1的结构强度、以及对于飞行效率的影响进行设置，在此不做具体限定。
同理的，在本实施例中，左侧进风风道8的结构与右侧进风风道8的结构相同。当然，在其他实施方式中，左侧进风风道8和右侧进风风道8的结构也可以有少许的变化，例如，左侧进风风道8的左通槽81和左导流板82均设置在左侧壁12c的顶端和底端的中间部分，右侧进风风道8的右通槽81设置在右侧壁12d的底部、右导流板82形成在下盖13的右侧边，本领域技术人员应该理解，这些简单替换均属于本发明的保护范围。
此外，应该理解，虽然上述实施例中介绍的上盖11、侧壁12、和下盖13为单独的三个部件，但也可以将上盖11与侧壁12通过一体成型形成一体件、或者将下盖13与侧壁12通过一体成型形成一体件，并且无需对进风风道8的结构作实质性的改变。
进一步，为了提高发热元件5和空气的热传递效果，在发热元件5和下盖13之间还设置有散热器7，该散热器7通过导热胶或者其他方式固定在发热元件5的底部。
图4为图1中散热器7的俯视图；图5为图1中散热器7的左视图；图6为图1中散热器7的仰视图。如图4至图6所示，散热器7可以是由金属制作而成的板状结构，其通过导热胶粘接在发热元件5的下部，发热元件5产生的热量通过导热胶传递到散热器7上。
工作时，无人机启动，螺旋桨3旋转，空气从螺旋桨3的桨叶旋转所 形成的平面的上方往下方流动从而形成桨风，经进风风道8进入到机壳1的容纳腔内，然后从散热器7的底面吹过，以与散热器7进行热交换，最后再从下盖13上开设的进风口流出机壳1，以便将发热元件5的热量带到机壳1外。
可选地，散热器7的底部形成有一个或者多个散热鳍71，以提高散热器7底面面积，从而提高散热效率。又可选地，散热器7上还设置有第二螺栓孔72，从而可以通过螺栓将散热器7与机壳1或者发热元件5(例如飞行控制电路板)固定，从而提高散热器7的连接强度。
进一步，为了避免发热元件5工作时的电磁场对无人机的其他发热元件5(例如动力组件的电调或者电机、云台的电机以及云台上安装的摄像头)产生电磁干扰，在散热器7和发热元件5之间还设置有电磁屏蔽板6。
图7为图1中下盖13的俯视图；图8为图1中下盖13的左视图；图9为图1中下盖13的仰视图。如图7至图9所示，下盖13沿散热器7的长度方向开设有多个长条形孔作为通风孔131，这多个长条形孔平行排列，以提高出风效果，继而提高散热效率。同时，这多个长条形孔可以沿散热器7的方向延伸，以配合散热器7底部的散热鳍71的结构，使得散热鳍71可能通过长条形孔而裸露，与外界冷空气直接接触，从而提高散热效率。
可以理解，通风孔131除了为上述说明的长条形孔以及排列形式，还可以为方形孔、圆孔、开窗中的一种或与之结合设计，通风孔131的形状、尺寸、密度以及排列形式可以多样化设计，能够配合散热器7对发热元件5进行散热即可，此处不做具体限定。
可选地，在下盖13上开设有多个第一螺栓孔132，通过螺栓将下盖13固定在容纳腔内的发热元件5上，例如将下盖13再与飞行控制电路板固定，以便提高飞行控制电路板的稳定性，避免其晃动。
脚架用于在无人机着落时支撑在地面或者地面定作物上，从而避免机壳1与地面或者地面定作物接触，以保护机壳1或者机壳1底部所安装的云台。其中，脚架可以与机壳1的下盖13固定，也可以设于机臂2的下方，还可以是机壳1的下盖13以及机臂2的下方配合设有脚架，该脚架可以为诸如软胶材质形成的缓冲结构。
最后应说明的是：以上实施方式仅用以说明本发明的技术方案，而非 对其进行限制；尽管参照前述实施方式对本发明已经进行了详细的说明，但本领域的普通技术人员应当理解：其依然可以对前述实施方式所记载的技术方案进行修改，或者对其中部分或者全部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实施方式技术方案的范围。

Claims (25)

  1. 一种无人机的机壳，所述机壳内置有所述无人机的发热元件，其特征在于，
    所述机壳上设置有进风风道，所述进风风道用于将所述螺旋桨旋转时产生的桨风导入所述机壳内；
    所述机壳的底部设有出风口，所述出风口用于将与所述发热元件进行热传递后的所述桨风导出所述机壳；
    其中，所述出风口被设置为用于与所述发热元件的散热器相配合的至少一个通孔。
  2. 根据权利要求1所述的机壳，其特征在于，所述机壳包括：侧壁、盖合在侧壁的上端开口处的上盖、以及盖合在侧壁的下端开口处的下盖；
    所述下盖上开设的所述通孔包括条形孔、方形孔、圆孔、开窗中的至少一种。
  3. 根据权利要求2所述的机壳，其特征在于，所述条形孔沿所述散热器的长度方向延伸。
  4. 根据权利要求2所述的机壳，其特征在于，所述进风风道包括：在所述侧壁上开设的通槽，以及设置在所述侧壁或者所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
  5. 根据权利要求2所述的机壳，其特征在于，所述进风风道包括：在所述下盖上开设的通槽，以及设置在所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
  6. 根据权利要求2所述的机壳，其特征在于，所述进风风道包括：在所述上盖上开设的通槽，以及设置在所述上盖、所述侧壁或者所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
  7. 根据权利要求4至6中任一项所述的机壳，其特征在于，所述导流板朝向所述通槽的内表面为弧面。
  8. 根据权利要求2至6中任一项所述的机壳，其特征在于，所述上盖和所述侧壁为一体成型的一体件，或者，所述下盖和所述侧壁为一体成型的一体件。
  9. 根据权利要求1至6中任一项所述的机壳，其特征在于，所述螺 旋桨旋转形成有旋转平面，所述进风风道在所述旋转平面上的正投影位于该旋转平面内。
  10. 根据权利要求1至6中任一项所述的机壳，其特征在于，所述进风风道设置在靠近所述机壳的前端的位置。
  11. 一种无人机，其特征在于，包括机壳、安装在所述机壳内的发热元件、螺旋桨、以及连接所述机壳与所述螺旋桨的机臂；
    所述机壳上设置有进风风道，所述进风风道用于将所述螺旋桨旋转时产生的桨风导入所述机壳内；
    所述机壳的底部设有出风口，所述出风口用于将与所述发热元件进行热传递后的所述桨风导出所述机壳；
    其中，所述出风口被设置为用于与所述发热元件的散热器相配合的至少一个通孔。
  12. 根据权利要求11所述的无人机，其特征在于，所述机壳包括：侧壁、盖合在侧壁的上端开口处的上盖、以及盖合在侧壁的下端开口处的下盖；
    所述下盖上开设的所述通孔包括条形孔、方形孔、圆孔、开窗中的至少一种。
  13. 根据权利要求12所述的无人机，其特征在于，所述条形孔沿所述散热器的长度方向延伸。
  14. 根据权利要求12所述的无人机，其特征在于，所述进风风道包括：在所述侧壁上开设的通槽，以及设置在所述侧壁或者所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
  15. 根据权利要求12所述的无人机，其特征在于，所述进风风道包括：在所述下盖上开设的通槽，以及设置在所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
  16. 根据权利要求12所述的无人机，其特征在于，所述进风风道包括：在所述上盖上开设的通槽，以及设置在所述上盖、所述侧壁或者所述下盖上的导流板；所述导流板从所述通槽往远离所述机壳的斜上方延伸。
  17. 根据权利要求14至16中任一项所述的无人机，其特征在于，所述导流板朝向所述通槽的内表面为弧面。
  18. 根据权利要求12至16中任一项所述的无人机，其特征在于，所述上盖和所述侧壁为一体成型的一体件，或者，所述下盖和所述侧壁为一体成型的一体件。
  19. 根据权利要求11至16中任一项所述的无人机，其特征在于，所述螺旋桨旋转形成有旋转平面，所述进风风道在所述旋转平面上的正投影位于该旋转平面内。
  20. 根据权利要求11至16中任一项所述的无人机，其特征在于，所述进风风道设置在靠近所述机壳的前端的位置。
  21. 根据权利要求11所述的无人机，其特征在于，所述发热元件和所述机壳的底部之间还设置有散热器，所述散热器固定在所述电子元件的底部。
  22. 根据权利要求21所述的无人机，其特征在于，所述散热器的底部设置有多个散热鳍。
  23. 根据权利要求11所述的无人机，其特征在于，所述机臂包括：第一支臂和第二支臂，且所述第一支臂和第二支臂之间具有夹角；
    所述第一支臂的第一端和所述第二支臂的第一端与所述螺旋桨连接，
    所述第一支臂的第二端和所述第二支臂的第二端分别与所述机壳连接。
  24. 根据权利要求23所述的无人机，其特征在于，所述第一支臂和第二支臂上开设有减重槽。
  25. 根据权利要求23所述的无人机，其特征在于，所述机壳的进风风道位于所述第一支臂和第二支臂之间。
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