WO2018209770A1 - 气压计组件及无人机 - Google Patents

气压计组件及无人机 Download PDF

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Publication number
WO2018209770A1
WO2018209770A1 PCT/CN2017/090948 CN2017090948W WO2018209770A1 WO 2018209770 A1 WO2018209770 A1 WO 2018209770A1 CN 2017090948 W CN2017090948 W CN 2017090948W WO 2018209770 A1 WO2018209770 A1 WO 2018209770A1
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WIPO (PCT)
Prior art keywords
mounting plate
front cover
barometer
disposed
bottom cover
Prior art date
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Ceased
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PCT/CN2017/090948
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English (en)
French (fr)
Inventor
梁贵彬
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201780065003.5A priority Critical patent/CN109843717B/zh
Publication of WO2018209770A1 publication Critical patent/WO2018209770A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D43/00—Arrangements or adaptations of instruments
    • 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
    • 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

Definitions

  • the present invention relates to the field of drones, and more particularly to a barometer assembly and a drone.
  • a barometer is usually installed on the drone.
  • the barometer is used to measure the atmospheric pressure information, and then the barometer data is transmitted to the flight controller. After the process, the current drone flight can be known.
  • the height further controls the flying height of the drone to a preset value, so that the aircraft does not generate unnecessary height errors when performing certain actions, thereby improving the stability and safety performance of the aircraft.
  • the position of the existing multi-rotor UAV's barometer makes it vulnerable to the strong airflow of the multi-rotor blade, which leads to inaccurate atmospheric pressure information obtained by the barometer, resulting in the flight controller to the drone.
  • the height estimate is inaccurate, which affects its control of the drone, resulting in poor control accuracy.
  • Embodiments of the present invention provide a barometer assembly and a drone.
  • a barometer assembly for an unmanned aerial vehicle comprising a center frame, an arm extending outward from the center frame, and a power assembly disposed on the arm;
  • the drones include:
  • a housing disposed on a lower side of the center frame, the housing is formed with a receiving cavity, and the receiving cavity is formed with a through hole located at a bottom surface of the housing and communicating the receiving cavity with the outside;
  • the barometer assembly includes at least one barometer disposed in the containment chamber.
  • the barometer is disposed in the receiving cavity, and the receiving cavity communicates with the outside through the through hole, and the position of the through hole is set to be far away from the power component to the greatest extent, thereby improving the detection accuracy of the barometer component, and
  • the hole can be further circumvented by the housing to further reduce the influence of the airflow generated by the power assembly on the barometer disposed in the receiving cavity.
  • the power assembly includes a motor and a rotor, the rotor being coupled to the motor, the motor driving the rotor to rotate, the rotor having a shaft that is substantially perpendicular to a bottom surface of the housing.
  • the housing is also shaped with a battery compartment.
  • the housing comprises:
  • An inner frame plate, the inner frame plate includes:
  • bottom cover disposed on the bottom cover mounting plate, the bottom cover including a bottom surface of the housing
  • the receiving cavity is formed between the bottom cover and the bottom cover mounting plate or between the bottom cover and the bottom cover mounting plate and between the front cover and the front cover mounting plate.
  • the number of battery compartments is two on each side of the intermediate partition.
  • the drone includes a battery management system disposed between the front cover mounting plate and the front cover;
  • the front cover is sealingly connected to the front cover mounting plate and the center frame.
  • a front cover sealing groove surrounding the periphery of the front cover mounting plate is disposed on a side of the front cover mounting plate opposite to the front cover, and the front cover sealing groove is filled with a front cover a waterproof rubber ring, the front cover waterproof rubber ring connecting the front cover and the front cover mounting plate.
  • the drone includes a circuit component disposed between the bottom cover mounting plate and the bottom cover;
  • the bottom cover is sealingly connected to the bottom cover mounting plate.
  • a side of the bottom cover mounting plate opposite to the bottom cover is provided with a bottom cover sealing groove surrounding the periphery of the bottom cover mounting plate, and the bottom cover sealing groove is filled with a bottom cover a waterproof rubber ring, the bottom cover waterproof rubber ring connecting the bottom cover and the bottom cover mounting plate.
  • the housing further includes a filter disposed in the through hole network.
  • the drone includes an ultrasonic component
  • the screen is a screen mounted to the bottom of the ultrasonic component.
  • At least one of the barometers is disposed between the front cover and the front cover mounting plate and/or between the bottom cover and the bottom cover mounting plate.
  • a housing disposed on a lower side of the center frame, the housing is formed with a receiving cavity, and the receiving cavity is formed with a through hole located at a bottom surface of the housing and communicating the receiving cavity with the outside;
  • the barometer assembly is disposed in the receiving cavity.
  • the air pressure gauge is disposed in the receiving cavity, and the receiving cavity communicates with the outside through the through hole, and the position of the through hole is set to be far away from the power component to the greatest extent, thereby improving the detection accuracy of the barometer component, and
  • the hole can be further circumvented by the housing to further reduce the influence of the airflow generated by the power assembly on the barometer disposed in the receiving cavity.
  • FIG. 1 is a perspective view of a drone according to some embodiments of the present invention.
  • FIG. 2 is a perspective view showing a part of a structure of a drone according to some embodiments of the present invention
  • FIG. 3 is a perspective view showing a part of a structure of a drone according to some embodiments of the present invention.
  • FIG. 4 is a schematic cross-sectional view showing a portion of a structure of a drone according to some embodiments of the present invention.
  • UAV 100 barometer assembly 10, barometer 12, center frame 20, arm 30, power assembly 40, motor 42, rotor 44, housing 50, bottom surface 51, through hole 512, housing cavity 52, first sub Cavity 522, second sub-cavity 524, battery compartment 53, inner frame plate 54, middle partition 542, front cover mounting plate 544, bottom cover mounting plate 546, front cover 55, bottom cover 56, strainer 57, battery management system 60, ultrasonic component 70.
  • first and second are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
  • features defining “first” or “second” may include one or more of the described features either explicitly or implicitly.
  • the meaning of "a plurality” is two or more unless specifically and specifically defined otherwise.
  • connection is to be understood broadly, and may be fixed or detachable, for example, unless otherwise explicitly defined and defined.
  • Connected, or connected in one piece; can be mechanical Connections may also be electrically connected or may communicate with each other; they may be directly connected or indirectly connected through an intermediate medium, and may be internal communication of two elements or an interaction relationship of two elements.
  • the specific meanings of the above terms in the present invention can be understood on a case-by-case basis.
  • the first feature "on” or “under” the second feature may include direct contact of the first and second features, and may also include first and second features, unless otherwise specifically defined and defined. It is not in direct contact but through additional features between them.
  • the first feature "above”, “above” and “above” the second feature includes the first feature directly above and above the second feature, or merely indicating that the first feature level is higher than the second feature.
  • the first feature “below”, “below” and “below” the second feature includes the first feature directly below and below the second feature, or merely the first feature level being less than the second feature.
  • a barometer assembly 10 according to an embodiment of the present invention is used in a drone 100.
  • the drone 100 includes a center frame 20, an arm 30 extending outward from the center frame 20, a power assembly 40 disposed on the arm 30, and a lower side disposed on the center frame 20.
  • the housing 50 is formed with a receiving cavity 52.
  • the receiving cavity 52 is formed with a through hole 512 located on the bottom surface 51 of the housing 50 and communicating with the receiving cavity 52 and the outside.
  • the barometer assembly 10 includes at least one barometer 12 disposed in the containment chamber 52.
  • the air pressure gauge 12 is disposed in the receiving cavity 52, and the receiving cavity 52 communicates with the outside through the through hole 512.
  • the position of the through hole 512 is disposed farthest away from the power component 40, and the barometer assembly 10 is improved.
  • the detection accuracy is further improved.
  • the through hole 512 can further reduce the power component 40 due to the shielding of the housing 50. The resulting airflow affects the barometer 12 disposed within the containment chamber 52.
  • the power assembly 40 drives the drone 100 to move by driving nearby airflow, which causes a change in nearby air pressure.
  • the power assembly 40 and the housing 50 are respectively located on opposite sides of the center frame 20.
  • the through holes 512 formed in the bottom of the housing 50 are spaced apart from the power assembly 40, effectively reducing the airflow generated by the power assembly 40 to the bottom of the housing 50.
  • the effect of the nearby air pressure further reduces the effect on the barometer 12 in the containment chamber 52.
  • the barometer assembly 10 can include a barometer 12 and can also include a plurality of barometers 12.
  • the number of the barometers 12 is plural, it helps to reduce the accidental error of the data, and further improves the detection accuracy of the barometer assembly 10.
  • the number of the barometers 12 is four, the measured data of the four barometers 12 are transmitted to the flight controller of the drone 100, and the flight controller will fuse the data, specifically It can be averaging, or averaging after removing outliers, and so on.
  • setting a plurality of barometers 12 is a redundant design consideration. For example, when one of the barometers 12 fails, the other barometers 12 operate normally, so that the barometer assembly 10 can still detect a more appropriate barometric pressure value. .
  • the power assembly 40 includes a motor 42 and a rotor 44 .
  • the rotor 44 is coupled to the motor 42 .
  • the motor 42 drives the rotor 44 to rotate.
  • the axis of rotation H of the rotor 44 is substantially perpendicular to the housing 50 .
  • the bottom surface 51 is substantially perpendicular to the housing 50 .
  • vertical means that the rotating shaft H is not completely perpendicular to the bottom surface 51 of the housing 50, but the angle formed therebetween is substantially close to 90°, and the intersection of the four rotating shafts H is located above the drone 100, so that each design is such that The plane of rotation of one of the rotors 44 is slightly inclined downward from the end of the arm 30 toward the center frame 20, so that the airflow generated by the rotation of each of the four rotors 44 is slightly inclined outward rather than vertically downward, thereby making four The airflow generated by the rotation of the rotor 44 is wider outside the center frame 20 and increases the stability of the flight of the drone 10.
  • the motor 42 drives the rotor 44 to rotate to provide power to the drone 100.
  • the air velocity near the rotor 44 is fast, forming a negative pressure, and the rotating shaft H of the rotor 44 is substantially perpendicular to the bottom surface 51 of the casing 50, so that the casing
  • the bottom surface 51 of the body 50 is farthest away from the rotor 44, and the air pressure near the bottom surface 51 of the casing 50 is substantially unaffected by the rotation of the rotor 44, and the receiving cavity 52 passes through the through hole provided at the bottom of the casing 50.
  • the 512 is in communication with the outside air such that the airflow generated by the rotor 44 has less effect on the barometer 12 disposed within the containment chamber 52.
  • the housing 50 is also shaped with a battery compartment 53.
  • the housing 50 is disposed on the lower side of the center frame 20, and the battery is placed in the battery compartment 53. Since the battery has a large self-weight, the center of gravity of the drone 100 can be lowered, which helps to make the drone 100 fly more smoothly.
  • the housing 50 includes:
  • the inner frame plate 54 and the inner frame plate 54 include:
  • the bottom cover 56 disposed on the bottom cover mounting plate 546, the bottom cover 56 includes a bottom surface 51 of the housing 50;
  • the receiving cavity 52 is formed between the bottom cover 56 and the bottom cover mounting plate 546 or between the bottom cover 56 and the bottom cover mounting plate 546 and between the front cover 55 and the front cover mounting plate 544.
  • the barometer 12 may be disposed between the bottom cover 56 and the bottom cover mounting plate 546, or may be disposed between the bottom cover 56 and the bottom cover mounting plate 546. At least one barometer 12 is disposed between each of the front cover 55 and the front cover mounting plate 544, and the barometer 12 is less affected by the airflow generated by the rotor 44.
  • the receiving cavity 52 includes a first sub-cavity 522 formed between the bottom cover 56 and the bottom cover mounting plate 546 and a second sub-cavity 524 disposed between the front cover 55 and the front cover mounting plate 544.
  • the first sub-cavity 522 and the second sub-cavity 524 are in communication, and at least one barometer 12 may be disposed only in the first sub-cavity 522, or at least one barometer 12 may be disposed in the second sub-cavity 524. At least one barometer 12 is disposed in each of a sub-cavity 522 and a second sub-cavity 524.
  • first sub-cavity 522 and the second sub-cavity 524 may also be disconnected, and at least one barometer 12 is disposed only in the first sub-cavity 522.
  • the number of battery compartments 53 is two in the middle partition 542 on both sides.
  • the two battery compartments 53 enable the drone 100 to carry two batteries at the same time, which helps to extend the life time of the drone 100 and improve the user experience.
  • the two battery compartments 53 are respectively located on both sides of the intermediate partition 542 such that the center of gravity of the housing 50 is close to the geometric center of the housing 50, which helps to improve the flight stability of the drone 100.
  • Two battery spacing settings reduce heat transfer between the two batteries and help to avoid excessive battery temperatures.
  • the drone 100 includes a battery management system 60 disposed between the front cover mounting plate 544 and the front cover 55;
  • the front cover 55 is sealingly coupled to the front cover mounting plate 544 and the center frame 20.
  • the front cover 55 is sealingly coupled to the front cover mounting plate 544 and the center frame 20 such that the battery management system 60 is protected from the impact of the airflow generated by the power assembly 40, helping to protect the battery management system 60.
  • the receiving cavity 52 formed between the front cover mounting plate 544 and the front cover 55 communicates with the outside atmosphere only through the through hole 512, thereby reducing the influence of the airflow generated by the power unit 40 on the barometer 12 disposed in the receiving cavity 52.
  • battery management system 60 can be used to monitor the status of the battery or to charge and discharge the battery.
  • battery management system 60 can take parameters such as voltage, current, and temperature of the battery and control these parameters.
  • a side of the front cover mounting plate 544 opposite to the front cover 55 is provided with a front cover sealing groove (not shown) surrounding the periphery of the front cover mounting plate 544, and the front cover sealing groove is filled with a front cover A waterproof apron (not shown), the front cover waterproof apron is connected to the front cover 55 and the front cover mounting plate 544.
  • the front cover 55 and the front cover mounting plate 544 are sealed to prevent impurities such as dust or/and water from entering between the front cover 55 and the front cover mounting plate 544 through the gap between the front cover 55 and the front cover mounting plate 544, and the protection setting is provided.
  • the front cover waterproof rubber ring can be made of waterproof elastic silicone.
  • the drone 100 includes circuit components disposed between the bottom cover mounting plate 546 and the bottom cover 56;
  • the bottom cover 56 is sealingly coupled to the bottom cover mounting plate 546.
  • the bottom cover 56 is sealingly connected to the bottom cover mounting plate 546 to prevent impurities such as dust or/and water from entering the bottom cover 56 through the gap between the bottom cover 56 and the bottom cover mounting plate 546.
  • the circuit components disposed between the bottom cover mounting plate 546 and the bottom cover 56 are affected between the bottom cover mounting plate 546 and the bottom cover mounting plate 546.
  • a side of the bottom cover mounting plate 546 opposite to the bottom cover 56 is provided with a bottom cover sealing groove (not shown) surrounding the periphery of the bottom cover mounting plate 546, and the bottom cover sealing groove is filled with a bottom cover A waterproof apron (not shown), the bottom cover waterproof apron is connected to the bottom cover 56 and the bottom cover mounting plate 546.
  • the bottom cover 56 and the bottom cover mounting plate 546 are sealed to prevent impurities such as dust or/and water from entering between the bottom cover 56 and the bottom cover mounting plate 546 through the gap between the bottom cover 56 and the bottom cover mounting plate 546, and the protection is provided at the bottom. Circuit elements between cover 56 and bottom cover mounting plate 546, such as barometer 12.
  • the bottom cover waterproof rubber ring can be made of waterproof elastic silicone.
  • the housing 50 also includes a screen 57 disposed within the through bore 512.
  • the screen 57 is a waterproof and breathable mesh. In this manner, while preventing impurities such as dust or/and water from entering the receiving cavity 52 through the through hole 512, the receiving cavity 52 is kept in communication with the outside atmosphere, so that the barometer assembly 10 disposed in the receiving cavity 52 can detect the air pressure in real time.
  • the drone 100 includes an ultrasonic assembly 70 that is a screen 57 that is mounted to the bottom of the ultrasonic assembly 70.
  • the through hole 512 allows the ultrasonic assembly 70 to emit ultrasonic waves to the outside of the housing 50 and to receive the transmitted ultrasonic waves.
  • the ultrasonic component 70 is disposed in the housing cavity 52, and transmits and receives ultrasonic waves for ranging. Ultrasonic waves pass through the through holes 512.
  • a filter 57 is provided at the bottom of the ultrasonic component 70 for preventing the entry of impurities such as dust or/and water.
  • At least one barometer 12 is disposed between the front cover 55 and the front cover mounting plate 544 and/or between the bottom cover 56 and the bottom cover mounting plate 546.
  • the barometer 12 is disposed between the front cover 55 and the front cover mounting plate 544 and/or between the bottom cover 56 and the bottom cover mounting plate 546, so that when the barometer 12 detects air pressure, it is rotated.
  • the effect of the airflow generated by the wings 44 is small.
  • one or more barometers 12 may be provided between the front cover 55 and the front cover mounting plate 544.
  • One or more barometers 12 may also be provided between the bottom cover 56 and the bottom cover mounting plate 546.
  • One or more barometers 12 may also be disposed between the front cover 55 and the front cover mounting plate 544, while one or more barometers 12 are also disposed between the bottom cover 56 and the bottom cover mounting plate 546.
  • a drone 100 includes:
  • An arm 30 extending outward from the center frame 20;
  • the housing 50 is disposed on the lower side of the center frame 20, and the housing 50 is formed with a receiving cavity 52.
  • the receiving cavity 52 is formed with a through hole 512 located at the bottom surface 51 of the housing 50 and communicating with the receiving cavity 52 and the outside;
  • the barometer assembly 10 is disposed in the housing chamber 52.
  • the air pressure gauge 12 is disposed in the receiving cavity 52, and the receiving cavity 52 communicates with the outside through the through hole 512.
  • the position of the through hole 512 is disposed farthest away from the power component 40, and the barometer assembly 10 is improved.
  • the through hole 512 can further reduce the influence of the airflow generated by the power component 40 on the barometer 12 disposed in the receiving cavity 52 due to the shielding of the housing 50.
  • 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 at least one feature, either explicitly or implicitly.
  • a plurality means at least two, for example two, three, unless specifically defined otherwise.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Mechanical Engineering (AREA)
  • Measuring Fluid Pressure (AREA)

Abstract

一种气压计组件（10）及无人机（100），气压计组件（10）用于无人机（100），无人机（100）包括中心架（20）、自所述中心架（20）向外延伸的机臂（30）、设置在所述机臂（30）上的动力组件（40）和设置在所述中心架（20）下侧的壳体（50），所述壳体（50）形成有收容腔（52），所述收容腔（52）形成有位于所述壳体（50）的底面（51）且连通所述收容腔（52）与外界的通孔（512）；所述气压计组件（10）包括设置于所述收容腔（52）的至少一个气压计（12），由于气压计（12）设置于收容腔（52）内，收容腔（52）通过通孔（512）与外界连通，通孔（512）的位置设置最大程度上远离动力组件（40），提高气压计组件（10）的检测准确度，另外，通孔（512）由于受到壳体（50）的遮挡可以进一步减少动力组件（40）产生的气流对设置在收容腔（52）内的气压计（512）的影响。

Description

气压计组件及无人机 技术领域
本发明涉及无人机领域，尤其是涉及一种气压计组件和无人机。
背景技术
现有技术中，通常在无人机上设置气压计，气压计用来测量大气的气压信息，然后把气压计的数据传输至飞行控制器上，经过处理后，可以得知目前无人机的飞行高度进而控制无人机的飞行高度使其达到预设值，使飞行器在执行特定动作时不会产生不必要的高度误差，从而提高飞行器的稳定性能和安全性能。
然而现有的多旋翼无人飞行器的气压计的设置位置使其容易受到多旋翼桨叶强大的气流影响，从而导致气压计获取的大气的气压信息不准确，从而导致飞行控制器对无人机的高度预估不准确，从而影响其对无人机的控制，导致控制的准确度差。
发明内容
本发明的实施方式提供一种气压计组件及无人机。
本发明实施方式的一种气压计组件，用于无人机，所述无人机包括中心架、自所述中心架向外延伸的机臂和设置在所述机臂上的动力组件；所述无人机包括：
设置在所述中心架下侧的壳体，所述壳体形成有收容腔，所述收容腔形成有位于所述壳体的底面且连通所述收容腔与外界的通孔；
所述气压计组件包括设置于所述收容腔的至少一个气压计。
本发明实施方式的气压计组件，气压计设置于收容腔内，收容腔通过通孔与外界连通，通孔的位置设置最大程度上远离动力组件，提高气压计组件的检测准确度，另外，通孔由于受到壳体的遮挡可以进一步减少动力组件产生的气流对设置在收容腔内的气压计的影响。
在某些实施方式中，所述动力组件包括电机和旋翼，所述旋翼与所述电机连接，所述电机驱动所述旋翼旋转，所述旋翼的转轴基本垂直于所述壳体的底面。
在某些实施方式中，所述壳体还形有电池仓。
在某些实施方式中，所述壳体包括：
内框板，所述内框板包括：
竖直设置的中隔板；
设置所述中隔板前侧的前盖安装板；
设置在所述中隔板底端的底盖安装板，
设置在所述前盖安装板上的前盖；和
设置在所述底盖安装板上的底盖，所述底盖包括所述壳体的底面；
所述收容腔形成于所述底盖与所述底盖安装板之间或所述底盖与所述底盖安装板之间和所述前盖和所述前盖安装板之间。
在某些实施方式中，所述电池仓的数目为两个分别位于所述中隔板两侧。
在某些实施方式中，所述无人机包括设置在所述前盖安装板与所述前盖之间的电池管理系统；
所述前盖与所述前盖安装板和所述中心架密封连接。
在某些实施方式中，所述前盖安装板的与所述前盖相对的一面上设置有环绕所述前盖安装板周缘的前盖密封槽，所述前盖密封槽内填充有前盖防水胶圈，所述前盖防水胶圈连接所述前盖和所述前盖安装板。
在某些实施方式中，所述无人机包括设置在所述底盖安装板与所述底盖之间的电路元件；
所述底盖与所述底盖安装板密封连接。
在某些实施方式中，所述底盖安装板的与所述底盖相对的一面上设置有环绕所述底盖安装板周缘的底盖密封槽，所述底盖密封槽内填充有底盖防水胶圈，所述底盖防水胶圈连接所述底盖和所述底盖安装板。
在某些实施方式中，所述壳体还包括设置在所述通孔内的滤 网。
在某些实施方式中，所述无人机包括超声波组件，所述滤网为所述超声波组件的底部装设的滤网。
在某些实施方式中，至少一个所述气压计设置在所述前盖与所述前盖安装板之间和/或所述底盖与所述底盖安装板之间。
本发明实施方式的一种无人机包括：
中心架；
自所述中心架向外延伸的机臂；
设置在所述机臂上的动力组件；
设置在所述中心架下侧的壳体，所述壳体形成有收容腔，所述收容腔形成有位于所述壳体的底面且连通所述收容腔与外界的通孔；和
上述任一实施方式所述的气压计组件，所述气压计组件设置在所述收容腔内。
本发明实施方式的无人机，气压计设置于收容腔内，收容腔通过通孔与外界连通，通孔的位置设置最大程度上远离动力组件，提高气压计组件的检测准确度，另外，通孔由于受到壳体的遮挡可以进一步减少动力组件产生的气流对设置在收容腔内的气压计的影响。
本发明的实施方式的附加方面和优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本发明的实施方式的实践了解到。
附图说明
本发明的实施方式的上述和/或附加的方面和优点从结合下面附图对实施方式的描述中将变得明显和容易理解，其中：
图1是本发明某些实施方式提供的无人机立体示意图；
图2是本发明某些实施方式提供的无人机部分结构的立体示意图；
图3是本发明某些实施方式提供的无人机部分结构的立体示意图；
图4是本发明某些实施方式提供的无人机部分结构的截面示意图。
主要元件符号说明：
无人机100，气压计组件10，气压计12，中心架20，机臂30，动力组件40，电机42，旋翼44，壳体50，底面51，通孔512，收容腔52，第一子腔522，第二子腔524，电池仓53，内框板54，中隔板542，前盖安装板544，底盖安装板546，前盖55，底盖56，滤网57，电池管理系统60，超声波组件70。
具体实施方式
下面详细描述本发明的实施方式，所述实施方式的示例在附图中示出，其中自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。下面通过参考附图描述的实施方式是示例性的，仅用于解释本发明，而不能理解为对本发明的限制。
在本发明的描述中，需要理解的是，术语“中心”、“纵向”、“横向”、“长度”、“宽度”、“厚度”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”、“顺时针”、“逆时针”指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括一个或者更多个所述特征。在本发明的描述中，“多个”的含义是两个或两个以上，除非另有明确具体的限定。
在本发明的描述中，需要说明的是，除非另有明确的规定和限定，术语“安装”、“相连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接；可以是机械 连接，也可以是电连接或可以相互通讯；可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通或两个元件的相互作用关系。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本发明中的具体含义。
在本发明中，除非另有明确的规定和限定，第一特征在第二特征之“上”或之“下”可以包括第一和第二特征直接接触，也可以包括第一和第二特征不是直接接触而是通过它们之间的另外的特征接触。而且，第一特征在第二特征“之上”、“上方”和“上面”包括第一特征在第二特征正上方和斜上方，或仅仅表示第一特征水平高度高于第二特征。第一特征在第二特征“之下”、“下方”和“下面”包括第一特征在第二特征正下方和斜下方，或仅仅表示第一特征水平高度小于第二特征。
下文的公开提供了许多不同的实施方式或例子用来实现本发明的不同结构。为了简化本发明的公开，下文中对特定例子的部件和设置进行描述。当然，它们仅仅为示例，并且目的不在于限制本发明。此外，本发明可以在不同例子中重复参考数字和/或参考字母，这种重复是为了简化和清楚的目的，其本身不指示所讨论各种实施方式和/或设置之间的关系。此外，本发明提供了的各种特定的工艺和材料的例子，但是本领域普通技术人员可以意识到其他工艺的应用和/或其他材料的使用。
请参阅图1及图2，本发明实施方式的一种气压计组件10，用于无人机100。
请一并参阅图1-图4，无人机100包括中心架20、自中心架20向外延伸的机臂30、设置在机臂30上的动力组件40和设置在中心架20下侧的壳体50，壳体50形成有收容腔52，收容腔52形成有位于壳体50的底面51且连通收容腔52与外界的通孔512。
气压计组件10包括设置于收容腔52的至少一个气压计12。
本发明实施方式的气压计组件10，气压计12设置于收容腔52内，收容腔52通过通孔512与外界连通，通孔512的位置设置最大程度上远离动力组件40，提高气压计组件10的检测准确度，另外，通孔512由于受到壳体50的遮挡可以进一步减少动力组件40 产生的气流对设置在收容腔52内的气压计12的影响。
可以理解，动力组件40通过带动附近气流流动驱动无人机100运动，气流流动会导致附近的气压变化。动力组件40与壳体50分别位于中心架20相背的两侧，形成于壳体50底部的通孔512与动力组件40间隔设置，有效地减小动力组件40产生的气流对壳体50底部附近气压的影响，进而减小对收容腔52内的气压计12的影响。
具体地，气压计组件10可以包括一个气压计12，也可以包括多个气压计12。当气压计12为多个时，有助于降低数据的偶然误差，进一步地提高气压计组件10的检测准确度。例如，当气压计12的数量为四个时，所述四个气压计12所测得的数据均传输给无人机100的飞行控制器，飞行控制器会对这些数据进行融合处理，具体的可以是求平均值，或者剔除异常值后进行平均，等等。另一方面，设置多个气压计12为冗余设计考虑，例如，当其中一个气压计12故障时，其他气压计12正常工作也可以使得气压计组件10仍然可以检测到一个较为合适的气压值。
请参阅图1及图4，在某些实施方式中，动力组件40包括电机42和旋翼44，旋翼44与电机42连接，电机42驱动旋翼44旋转，旋翼44的转轴H基本垂直于壳体50的底面51。基本垂直是指转轴H与壳体50的底面51并非完全垂直，而是两者之间形成的角度基本接近90°，且四个转轴H的交点位于无人机100的上方，如此设计使得每一个旋翼44的旋转平面均是从机臂30的端部朝向中心架20方向稍稍向下倾斜，从而使四个旋翼44各自转动产生的气流稍稍向外倾斜而非垂直向下，进而使得四个旋翼44转动产生的气流在中心架20的下方的辐射区域更广而增加无人机10飞行的稳定性。
如此，电机42驱动旋翼44旋转为无人机100提供动力，旋翼44旋转时，旋翼44附近的空气流速快，形成负压，旋翼44的转轴H基本垂直于壳体50的底面51，使得壳体50的底面51最大程度上远离旋翼44，壳体50的底面51附近的气压基本不受旋翼44转动的影响，又由于收容腔52通过设置在壳体50底部的通孔 512与外界空气连通，使得旋翼44产生的气流对设置在收容腔52内的气压计12的影响较小。
请参阅图1及图2，在某些实施方式中，壳体50还形有电池仓53。
如此，壳体50设置在中心架20下侧，电池置于电池仓53内，由于电池自重较大，可降低无人机100的重心，有助于使得无人机100飞行更加平稳。
请参阅图2及图4，在某些实施方式中，壳体50包括：
内框板54，内框板54包括：
竖直设置的中隔板542；
设置中隔板542前侧的前盖安装板544；
设置在中隔板542底端的底盖安装板546，
设置在前盖安装板544上的前盖55；和
设置在底盖安装板546上的底盖56，底盖56包括壳体50的底面51；
收容腔52形成于底盖56与底盖安装板546之间或底盖56与底盖安装板546之间和前盖55和前盖安装板544之间。
如此，收容腔52通过底盖56上的通孔512与外部空气连通，气压计12可设置在底盖56与底盖安装板546之间，也可以在底盖56与底盖安装板546之间和前盖55和前盖安装板544之间各设置至少一个气压计12，气压计12受旋翼44产生的气流的影响较小。
具体地，收容腔52包括形成于底盖56与底盖安装板546之间的第一子腔522和设置于前盖55和前盖安装板544之间的第二子腔524。第一子腔522和第二子腔524连通，可仅在第一子腔522内设置至少一个气压计12，也可以仅在第二子腔524内设置至少一个气压计12，还可以在第一子腔522和第二子腔524内各设置至少一个气压计12。
当然，在其他实施方式中，第一子腔522和第二子腔524也可以不连通，此时仅在第一子腔522内设置至少一个气压计12。
在某些实施方式中，电池仓53的数目为两个分别位于中隔板 542两侧。
如此，两个电池仓53使得无人机100可同时搭载两个电池，有助于延长无人机100的续航时间，提升用户体验。两个电池仓53分别位于中隔板542的两侧使得壳体50的重心接近壳体50的几何中心，有助于提高无人机100的飞行稳定性。两个电池间隔设置，可降低两个电池之间的热传导作用，有助于避免电池温度过高。
在某些实施方式中，无人机100包括设置在前盖安装板544与前盖55之间的电池管理系统60；
前盖55与前盖安装板544和中心架20密封连接。
如此，前盖55与前盖安装板544和中心架20密封连接使得电池管理系统60免受动力组件40产生的气流的冲击，有助于保护电池管理系统60。另外，形成于前盖安装板544与前盖55之间的收容腔52仅通过通孔512与外部大气连通，减少动力组件40产生的气流对设置在收容腔52内的气压计12的影响。
具体地，电池管理系统60可用于监测电池的状态或对电池进行充放电管理。例如，电池管理系统60可以获取电池的电压、电流和温度等参数，并对这些参数进行管控。
在某些实施方式中，前盖安装板544的与前盖55相对的一面上设置有环绕前盖安装板544周缘的前盖密封槽(图未示)，前盖密封槽内填充有前盖防水胶圈(图未示)，前盖防水胶圈连接前盖55和前盖安装板544。
如此，密封前盖55和前盖安装板544，避免灰尘或/及水等杂质通过前盖55和前盖安装板544之间的间隙进入前盖55和前盖安装板544之间，保护设置在前盖55和前盖安装板544之间的元器件，例如电池管理系统60。
具体地，前盖防水胶圈可以采用防水的弹性硅胶制成。
在某些实施方式中，无人机100包括设置在底盖安装板546与底盖56之间的电路元件；
底盖56与底盖安装板546密封连接。
如此，底盖56与底盖安装板546密封连接，可避免灰尘或/及水等杂质通过底盖56和底盖安装板546之间的间隙进入底盖56 和底盖安装板546之间对设置在底盖安装板546与底盖56之间的电路元件造成影响。
在某些实施方式中，底盖安装板546的与底盖56相对的一面上设置有环绕底盖安装板546周缘的底盖密封槽(图未示)，底盖密封槽内填充有底盖防水胶圈(图未示)，底盖防水胶圈连接底盖56和底盖安装板546。
如此，密封底盖56和底盖安装板546，避免灰尘或/及水等杂质通过底盖56和底盖安装板546的间隙进入底盖56和底盖安装板546之间，保护设置在底盖56和底盖安装板546之间的电路元件，例如气压计12。
具体地，底盖防水胶圈可以采用防水的弹性硅胶制成。
在某些实施方式中，壳体50还包括设置在通孔512内的滤网57。
如此，避免灰尘或/及水等杂质通过通孔512进入收容腔52，有助于保持收容腔52洁净，延长收容腔52的清理周期，保护设置在收容腔52内的元器件，例如气压计12、电池管理系统60等。
具体地，滤网57为防水透气网。如此，在阻止灰尘或/及水等杂质通过通孔512进入收容腔52的同时，收容腔52保持与外界大气连通，使设置在收容腔52内的气压计组件10可实时地检测气压。
在某些实施方式中，无人机100包括超声波组件70，滤网57为超声波组件70的底部装设的滤网57。
如此，通孔512使得超声波组件70可发射超声波至壳体50外和接回传的收超声波。
具体地，超声波组件70设置在收容腔52内，发射和接收超声波用于测距。超声波从通孔512通过。超声波组件70的底部设置滤网57用于阻止灰尘或/及水等杂质进入。
在某些实施方式中，至少一个气压计12设置在前盖55与前盖安装板544之间和/或底盖56与底盖安装板546之间。
如此，气压计12设置在前盖55与前盖安装板544之间和/或底盖56与底盖安装板546之间，使气压计12检测气压时，受旋 翼44产生的气流的影响较小。
可以理解，可以设置一个或者多个气压计12在前盖55与前盖安装板544之间。也可以设置一个或多个气压计12在底盖56与底盖安装板546之间。还可以在前盖55与前盖安装板544之间设置一个或多个气压计12，同时也在底盖56与底盖安装板546之间设置一个或多个气压计12。
请一并参阅图1-图4，本发明实施方式的一种无人机100包括：
中心架20；
自中心架20向外延伸的机臂30；
设置在机臂30上的动力组件40；
设置在中心架20下侧的壳体50，壳体50形成有收容腔52，收容腔52形成有位于壳体50的底面51且连通收容腔52与外界的通孔512；和
上述任一实施方式的气压计组件10，气压计组件10设置在收容腔52内。
本发明实施方式的无人机100，气压计12设置于收容腔52内，收容腔52通过通孔512与外界连通，通孔512的位置设置最大程度上远离动力组件40，提高气压计组件10的检测准确度，另外，通孔512由于受到壳体50的遮挡可以进一步减少动力组件40产生的气流对设置在收容腔52内的气压计12的影响。
在本说明书的描述中，参考术语“某些实施方式”、“一个实施方式”、“一些实施方式”、“示意性实施方式”、“示例”、“具体示例”、或“一些示例”的描述意指结合实施方式或示例描述的具体特征、结构、材料或者特点包含于本发明的至少一个实施方式或示例中。在本说明书中，对上述术语的示意性表述不一定指的是相同的实施方式或示例。而且，描述的具体特征、结构、材料或者特点可以在任何的一个或多个实施方式或示例中以合适的方式结合。
此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。 由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括至少一个特征。在本发明的描述中，“多个”的含义是至少两个，例如两个，三个，除非另有明确具体的限定。
尽管上面已经示出和描述了本发明的实施例，可以理解的是，上述实施例是示例性的，不能理解为对本发明的限制，本领域的普通技术人员在本发明的范围内可以对上述实施例进行变化、修改、替换和变型，本发明的范围由权利要求及其等同物限定。

Claims (13)

  1. 一种气压计组件，用于无人机，所述无人机包括中心架、自所述中心架向外延伸的机臂和设置在所述机臂上的动力组件；其特征在于，所述无人机包括：
    设置在所述中心架下侧的壳体，所述壳体形成有收容腔，所述收容腔形成有位于所述壳体的底面且连通所述收容腔与外界的通孔；
    所述气压计组件包括设置于所述收容腔的至少一个气压计。
  2. 根据权利要求1所述的气压计组件，其特征在于，所述动力组件包括电机和旋翼，所述旋翼与所述电机连接，所述电机驱动所述旋翼旋转，所述旋翼的转轴基本垂直于所述壳体的底面。
  3. 根据权利要求1所述的气压计组件，其特征在于，所述壳体还形有电池仓。
  4. 根据权利要求3所述的气压计组件，其特征在于，所述壳体包括：
    内框板，所述内框板包括：
    竖直设置的中隔板；
    设置所述中隔板前侧的前盖安装板；
    设置在所述中隔板底端的底盖安装板；
    设置在所述前盖安装板上的前盖；和
    设置在所述底盖安装板上的底盖，所述底盖包括所述壳体的底面；
    所述收容腔形成于所述底盖与所述底盖安装板之间或所述底盖与所述底盖安装板之间和所述前盖和所述前盖安装板之间。
  5. 根据权利要求4所述的气压计组件，其特征在于，所述电池仓的数目为两个分别位于所述中隔板两侧。
  6. 根据权利要求4所述的气压计组件，其特征在于，所述无人机包括设置在所述前盖安装板与所述前盖之间的电池管理系统；
    所述前盖与所述前盖安装板和所述中心架密封连接。
  7. 根据权利要求4所述的气压计组件，其特征在于，所述前盖安装板的与所述前盖相对的一面上设置有环绕所述前盖安装板 周缘的前盖密封槽，所述前盖密封槽内填充有前盖防水胶圈，所述前盖防水胶圈连接所述前盖和所述前盖安装板。
  8. 根据权利要求4所述的气压计组件，其特征在于，所述无人机包括设置在所述底盖安装板与所述底盖之间的电路元件；
    所述底盖与所述底盖安装板密封连接。
  9. 根据权利要求8所述的气压计组件，其特征在于，所述底盖安装板的与所述底盖相对的一面上设置有环绕所述底盖安装板周缘的底盖密封槽，所述底盖密封槽内填充有底盖防水胶圈，所述底盖防水胶圈连接所述底盖和所述底盖安装板。
  10. 根据权利要求1所述的气压计组件，其特征在于，所述壳体还包括设置在所述通孔内的滤网。
  11. 根据权利要求10所述的气压计组件，其特征在于，所述无人机包括超声波组件，所述滤网为所述超声波组件的底部装设的滤网。
  12. 根据权利要求4所述的气压计组件，其特征在于，至少一个所述气压计设置在所述前盖与所述前盖安装板之间和/或所述底盖与所述底盖安装板之间。
  13. 一种无人机，其特征在于包括：
    中心架；
    自所述中心架向外延伸的机臂；
    设置在所述机臂上的动力组件；
    设置在所述中心架下侧的壳体，所述壳体形成有收容腔，所述收容腔形成有位于所述壳体的底面且连通所述收容腔与外界的通孔；和
    如权利要求1-12任一项所述的气压计组件，所述气压计组件设置在所述收容腔内。
PCT/CN2017/090948 2017-05-19 2017-06-29 气压计组件及无人机 Ceased WO2018209770A1 (zh)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114414318A (zh) * 2022-01-24 2022-04-29 唐山市生态环境局曹妃甸区分局 一种基于无人机平台的大气环境样品采集装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109923040A (zh) * 2017-06-30 2019-06-21 深圳市大疆创新科技有限公司 无人飞行器及无人飞行器的组装方法
CN111322984B (zh) * 2020-04-15 2023-10-03 深圳市创客火科技有限公司 海拔高度计算方法及装置、无人机、存储介质

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6840480B2 (en) * 2001-09-27 2005-01-11 Ernest A. Carroll Miniature, unmanned aircraft with interchangeable data module
CN204121762U (zh) * 2014-09-23 2015-01-28 彭信泉 一种多旋翼飞行器
CN205015666U (zh) * 2015-09-24 2016-02-03 零度智控（北京）智能科技有限公司 无人机飞行控制器
CN105539847A (zh) * 2016-01-06 2016-05-04 陈昊哲 一种水空两栖无人机
CN205707333U (zh) * 2016-05-27 2016-11-23 深圳市汇金智能科技有限公司 一种四轴飞行器
CN106379521A (zh) * 2016-09-20 2017-02-08 东莞飞侠智能科技股份有限公司 一种智能无人飞机
CN206114183U (zh) * 2016-10-13 2017-04-19 深圳市大疆创新科技有限公司 感测组件及具有该感测组件的电子装置、无人机

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101382426A (zh) * 2007-09-05 2009-03-11 中国科学院自动化研究所 一种无人直升机自动导航系统
CN105912003B (zh) * 2016-06-23 2018-07-20 北京理工大学 垂直起降无人机自主着舰的辅助系统及方法
CN205957985U (zh) * 2016-08-26 2017-02-15 北京臻迪机器人有限公司 一种集气压检测的惯性测量装置

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6840480B2 (en) * 2001-09-27 2005-01-11 Ernest A. Carroll Miniature, unmanned aircraft with interchangeable data module
CN204121762U (zh) * 2014-09-23 2015-01-28 彭信泉 一种多旋翼飞行器
CN205015666U (zh) * 2015-09-24 2016-02-03 零度智控（北京）智能科技有限公司 无人机飞行控制器
CN105539847A (zh) * 2016-01-06 2016-05-04 陈昊哲 一种水空两栖无人机
CN205707333U (zh) * 2016-05-27 2016-11-23 深圳市汇金智能科技有限公司 一种四轴飞行器
CN106379521A (zh) * 2016-09-20 2017-02-08 东莞飞侠智能科技股份有限公司 一种智能无人飞机
CN206114183U (zh) * 2016-10-13 2017-04-19 深圳市大疆创新科技有限公司 感测组件及具有该感测组件的电子装置、无人机

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114414318A (zh) * 2022-01-24 2022-04-29 唐山市生态环境局曹妃甸区分局 一种基于无人机平台的大气环境样品采集装置

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