[go: up one dir, main page]

WO2018058329A1 - 可移动装置 - Google Patents

可移动装置 Download PDF

Info

Publication number
WO2018058329A1
WO2018058329A1 PCT/CN2016/100438 CN2016100438W WO2018058329A1 WO 2018058329 A1 WO2018058329 A1 WO 2018058329A1 CN 2016100438 W CN2016100438 W CN 2016100438W WO 2018058329 A1 WO2018058329 A1 WO 2018058329A1
Authority
WO
WIPO (PCT)
Prior art keywords
navigation antenna
antenna
movable device
navigation
mobile device
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2016/100438
Other languages
English (en)
French (fr)
Inventor
胡孟
熊荣明
陈日松
熊贤武
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
Original Assignee
SZ DJI 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 SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201680002573.5A priority Critical patent/CN106797070B/zh
Priority to PCT/CN2016/100438 priority patent/WO2018058329A1/zh
Priority to CN202010121566.5A priority patent/CN111313142B/zh
Publication of WO2018058329A1 publication Critical patent/WO2018058329A1/zh
Priority to US16/365,971 priority patent/US11171413B2/en
Anticipated expiration legal-status Critical
Priority to US17/490,560 priority patent/US20220021106A1/en
Ceased legal-status Critical Current

Links

Images

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/12—Supports; Mounting means
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/286—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/285—Aircraft wire antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/48—Earthing means; Earth screens; Counterpoises
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
    • H01Q3/04—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying one co-ordinate of the orientation
    • H01Q3/06—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying one co-ordinate of the orientation over a restricted angle

Definitions

  • the present invention relates to the field of aircraft technology, and in particular, to a movable device.
  • the navigation antenna is an important component of the mobile device and is typically mounted horizontally on top of the geometric center of the mobile device for receiving radio signals transmitted by the satellite and for converting the radio signals by the receiver.
  • the metal profile of the movable device acts as a reflective surface for the navigation antenna.
  • the appearance of mobile devices is diversified, and the navigation antennas are conformal to the movable device to avoid additional aerodynamic drag on the flight of the mobile device.
  • the navigation antenna is mounted on the top of the geometric center of the movable device, and the metal shape of the non-regularly shaped movable device guides the direction of the navigation antenna, thereby changing the orientation of the navigation antenna.
  • the conventional method reduces the change of the pattern by changing the shape of the navigation antenna and re-evaluating various parameters of the navigation antenna.
  • the above process of preventing the change of the pattern is achieved by changing the shape of the navigation antenna.
  • changing the shape of the navigation antenna will inevitably lead to changes in the antenna efficiency of the navigation antenna, and the purpose of improving the direction of the antenna while improving the efficiency of the antenna cannot be achieved.
  • Embodiments of the present invention provide a mobile device that achieves the purpose of improving the efficiency of an antenna while improving the direction of the antenna by tilting the navigation antenna at an edge portion of the movable device.
  • an embodiment of the present invention provides a mobile device including a body; and a navigation antenna disposed at an edge portion of the body; wherein the navigation antenna is disposed obliquely with respect to the body The height of one side of the navigation antenna near the center of the fuselage is greater than the other side of the navigation antenna away from the center of the fuselage.
  • a movable device provided by an embodiment of the present invention includes a body and a side disposed obliquely on the side of the body
  • the navigation antenna of the edge portion has a height closer to one side of the center portion of the airframe than to the other side of the center portion of the navigation antenna away from the body.
  • the fuselage exhibits a capacitive orientation
  • the direction of the navigation antenna is shifted toward the center of the fuselage, and the tilt direction of the navigation antenna is away from the center of the fuselage, so that the navigation antenna
  • the angle of the tilt is opposite to the angle of the antenna pattern, so it can compensate for the guiding effect of the irregular body on the navigation antenna, and achieve the purpose of ensuring the efficiency of the antenna while improving the direction.
  • Embodiment 1A is a schematic structural view of Embodiment 1 of a mobile device according to the present invention.
  • Figure 1B is an exploded view of Figure 1A;
  • 2A is a schematic diagram of a direction pattern of a navigation antenna when a navigation antenna of a shape-adjustable movable device is horizontally disposed;
  • 2B is a schematic diagram of a direction pattern of a navigation antenna when a navigation antenna of a non-regular shape movable device is horizontally disposed;
  • 2C is a schematic view showing the direction of the navigation antenna when the navigation antenna of the irregular shape of the movable device is tilted;
  • FIG. 3A is a schematic structural view of a second embodiment of a mobile device according to the present invention.
  • Figure 3B is an exploded view of Figure 3A;
  • Embodiment 3 is a schematic structural diagram of Embodiment 3 of a mobile device according to the present invention.
  • Figure 5 is a three-dimensional coordinate diagram of a movable device of the present invention.
  • FIG. 6A is a schematic structural view of a fourth embodiment of a mobile device according to the present invention.
  • Figure 6B is an exploded view of Figure 6A;
  • 7A is a simulation diagram of lobe gain when the navigation antenna is not tilted
  • Fig. 7B is a simulation diagram of lobe gain when the navigation antenna is tilted.
  • the navigation antenna is generally used as a built-in antenna, and is disposed at a central position inside the movable device casing, preferably at the center of the horizontal plane, in order to meet the aesthetic requirements of the unmanned aerial vehicle.
  • the housing of the movable device has a regular rectangular parallelepiped, and the navigation antenna is horizontally mounted at the top of the geometric center of the movable device, parallel to the plane formed by the pitch axis and the roll axis.
  • the appearance of mobile devices is diversified.
  • the shape of the movable device due to the shape of the movable device, there is no guarantee that the navigation antenna is mounted on top of the geometric center of the movable device. Since the reflective surface of the metal shape of the irregularly shaped movable device is weakened, the orientation of the navigation antenna is enhanced, so that the pattern of the navigation antenna is shifted.
  • the conventional method reduces the change of the pattern by changing the shape of the navigation antenna and re-evaluating various parameters of the navigation antenna.
  • the antenna efficiency of the navigation antenna is related to the projected area of the navigation antenna, the larger the projected area, the higher the antenna efficiency. If the shape of the navigation antenna is changed, the projected area of the navigation antenna changes, which causes the antenna efficiency of the navigation antenna to change, and the antenna efficiency cannot be ensured. At the same time, the purpose of improving the direction map.
  • the embodiment of the present invention provides a mobile device, which aims to improve the efficiency of the antenna while improving the direction of the antenna by tilting the navigation antenna at an edge portion of the movable device.
  • the movable device provided in this embodiment may specifically be an unmanned aerial vehicle, an unmanned vehicle, an unmanned ship, or the like.
  • a mobile device is taken as an unmanned aerial vehicle, and in particular, a multi-rotor unmanned aerial vehicle is described in detail.
  • FIG. 1A is a schematic structural diagram of Embodiment 1 of a mobile device according to the present invention.
  • the movable device provided in this embodiment includes: a body 1, and a navigation antenna 2.
  • a navigation antenna 2 is mounted on an edge portion of the body 1; wherein the navigation antenna 2 is disposed obliquely with respect to the body 1, such that the navigation antenna 2 is adjacent to a side of a center portion of the body 1.
  • the height is greater than the other side of the navigation antenna 2 away from the central portion of the fuselage 1.
  • the navigation antenna 2 for receiving a radio signal is conformally disposed with the body 1, and the navigation antenna 2 is installed at an edge portion of the interior of the body 1, and is disposed obliquely with respect to the body 1,
  • the direction of the tilt is opposite to the offset angle of the pattern of the navigation antenna 2.
  • the height of the side of the navigation antenna 2 near the center of the body 1 can be made larger than the height of the center of the navigation antenna 2 away from the center of the body 1. side.
  • the body 1 exhibits a capacitive guiding action, the pattern of the navigation antenna 2 is shifted toward the center portion of the body 1, and the tilting direction of the navigation antenna 2 is away from the center portion of the body 2.
  • FIG. 2A is a schematic diagram of a navigation antenna in a horizontally arranged movable device with a navigation antenna
  • FIG. 2B is a navigation antenna of an irregularly shaped movable device
  • FIG. 2C is a schematic diagram of the direction of the navigation antenna when the navigation antenna of the non-regular shape of the movable device is tilted.
  • the navigation antenna is disposed at the top of the geometric center of the movable device, parallel to the plane formed by the pitch axis and the roll axis, that is, the body shown in the figure. horizon. At this point, the pattern is not offset.
  • the navigation antenna is disposed at an end of the movable device, for example, a head and/or a tail.
  • the orientation pattern is shifted due to the guiding action of the irregularly shaped body 1.
  • the pattern is shifted to the left, that is, the radius of the pattern on the left side of the vertical dotted line is larger than the radius of the right side pattern.
  • the navigation antenna is tilted, and the tilt angle is opposite to the offset direction of the pattern in FIG. 2B, that is, offset to the right, which can be improved.
  • the side of the navigation antenna 2 near the center of the body 1 is such that the height of the navigation antenna 2 near the left side of the center portion of the body 1 is greater than the height of the navigation antenna 2 away from the right side of the center portion of the body 1.
  • the movable device provided by the embodiment of the present invention includes a body 1 and a navigation antenna 2 disposed obliquely at an edge portion of the body 1.
  • the height of the side of the navigation antenna 2 near the center of the body 1 is greater than that of the navigation antenna 2 The other side of the center of the fuselage 1.
  • the body 1 since the body 1 exhibits a capacitive guiding action, the pattern of the navigation antenna 2 is shifted toward the center portion of the body 1, and the tilting direction of the navigation antenna 2 is away from the center portion of the body 2.
  • the direction is such that the angle at which the navigation antenna 2 is tilted is opposite to the angle of the antenna pattern, so that the direction of the irregular antenna 1 to the navigation antenna 2 can be compensated for, and the purpose of improving the antenna efficiency while improving the antenna pattern can be achieved.
  • the navigation antenna 2 is specifically disposed at an end of the body 1.
  • it is disposed at the head of the movable device; for example, at the tail of the movable device; for example, the navigation antenna 2 is disposed at the head and the tail of the movable device.
  • the middle portion of the movable device is provided with a radiating element such as a battery. If the middle portion of the movable device is used as the geometric center of the movable device, the battery or the like occupies a position originally used for setting the navigation antenna 2.
  • the navigation antenna 2 is flexibly disposed on the head or the tail of the body 1, or the navigation antenna 2 is disposed on both the head and the tail, so that the navigation antenna 2 and the radiating elements such as the battery can coexist peacefully.
  • FIG. 1A, FIG. 3A and FIG. 4. 3A is a schematic structural view of a second embodiment of a mobile device according to the present invention, and FIG.
  • FIG. 4 is a schematic structural view of a third embodiment of the mobile device according to the present invention.
  • the navigation antenna 2 is disposed at the tail of the movable device.
  • the navigation antenna 2 is disposed at the head of the movable device.
  • the navigation antenna 2 is disposed at the head and the tail of the movable device. .
  • the navigation antenna 2 when the navigation antenna 2 is disposed at both the head and the tail of the movable device, the navigation antenna 2 includes a first navigation antenna 21 and a second navigation antenna 22, and the first navigation antenna 21 is disposed at the head of the movable device.
  • the second navigation antenna 22 is disposed at the tail of the movable device.
  • the first navigation antenna 21 operates; when the movable device retreats, the second navigation antenna 22 operates.
  • the present invention is not limited thereto.
  • the first navigation antenna 21 and the second navigation antenna 22 may also work simultaneously, for example, when both the first navigation antenna 21 and the second navigation antenna are In the case of a Real Time Kinematic (RTK) antenna, the first navigation antenna 21 and the second navigation antenna 22 operate simultaneously.
  • the first navigation antenna 21 and the second navigation antenna 22 may also be switched to each other. For example, when the mobile device is flying forward, the first navigation antenna 21 operates, and if the signal of the first navigation antenna 21 is weak, it can be switched to the second navigation antenna 22, and the second navigation antenna 22 receives the radio signal.
  • RTK Real Time Kinematic
  • the preset angle of the navigation antenna 2 tilted relative to the body 1 increases as the distance of the navigation antenna 2 from the center of the body 1 increases.
  • the middle dotted line is the center line of the movable device
  • the distance between the first navigation antenna 21 and the center portion of the body 1 is the distance 1
  • the first navigation antenna 22 is opposite to the pitch axis and the roll axis.
  • the predetermined tilt angle of the formed plane shown by the horizontal dashed line in FIG.
  • the distance between the second navigation antenna 22 and the center portion of the fuselage 1 is distance 2
  • the second navigation antenna 22 is relative to the pitch axis and
  • the preset inclination angle of the plane formed by the roll axis is ⁇ . Since the distance 1 is smaller than the distance 2, the predetermined angle at which the first navigation antenna 21 is inclined with respect to the body 1 is smaller than a predetermined angle at which the second navigation antenna 22 is inclined with respect to the body 1, that is, ⁇ .
  • the navigation antenna 2 is disposed at a side position of the body 1, such that the position of the navigation antenna 2 is not limited to the head or the tail of the movable device, and the navigation antenna 2 is implemented. Flexible settings.
  • FIG. 5 is a three-dimensional coordinate diagram applicable to the movable device of the present invention, wherein the X-axis, the Y-axis, and the Z-axis are respectively a pitch axis, a roll axis, and a yaw axis.
  • the navigation antenna 2 is disposed obliquely with respect to the body 1.
  • the navigation antenna 2 is compared to the roll of the movable device.
  • the plane formed by the axis and the pitch axis is inclined by a predetermined angle, and the preset angle is between 1 degree and 60 degrees.
  • the navigation antenna 2 is inclined by 5 degrees, 10 degrees, 12 degrees, 15 degrees, 18 degrees, 25 degrees, 28°, 30°, 35° 38°, 42°, 46°, 49°, 50°, 53°, 55°, 58°, 60°.
  • the tilt angle is between 30 degrees and 50 degrees, for example, 30 degrees, 33 degrees, 35°, 37°, 38.5°, 40°, 45°, 50°.
  • the navigation antenna 2 is compared to the body 1
  • the tilting arrangement in particular in the illustrated embodiment, the navigation antenna 2 is preset at an angle relative to the yaw axis of the movable device.
  • the preset angle is between 1 and 60 degrees, for example, 30, 32, 35, 38, 40, 42, 46, 48.6, 50, 52, 57, 60 °, 64, 67, 69, 70, 72, 74.7, 76, 79, 80, 83, 85.2, 86, 88, 89.
  • the angle is between 40 degrees and 60 degrees, such as 40 degrees, 45 degrees, 50 degrees, 53 degrees, 55 degrees. , 58 °, 60 °.
  • the navigation antenna 2 is disposed obliquely with respect to the body 1.
  • the navigation antenna 2 is parallel to the movable device.
  • the yaw axis setting, ie the navigation antenna 2 is arranged substantially parallel to the pitch axis of the movable device or completely parallel to the yaw axis of the movable device.
  • the navigation antenna 2 may be a right-handed antenna or the like from the perspective of antenna polarization; from the perspective of a frequency band, the above-mentioned navigation antenna 2 is a Global Positioning System (GPS) antenna or GLONASS antennas, Wi-Fi antennas, etc.
  • GPS Global Positioning System
  • GLONASS Global Positioning System
  • Wi-Fi Wireless Fidelity
  • the navigation antenna 2 is a GPS antenna, it is, for example, a Right Hand Circular Polarization (RHCP), so that the navigation antenna 2 smoothly receives a radio signal.
  • RHCP Right Hand Circular Polarization
  • the body 1 includes an outer casing and an electrical compartment, the electrical compartment is disposed at a middle portion of a top surface of the outer casing, and the navigation antenna 2 is disposed in the outer casing.
  • the outer casing of the fuselage 1 includes an upper cover 11 and a lower cover 12 disposed opposite to each other.
  • the upper cover and the lower cover are disposed to form an accommodating space, and the electrical storage compartment 3 is located in the accommodating space.
  • the navigation antenna 2 is located at an edge portion in the accommodation space, such as the head and/or the tail in the accommodation space.
  • the electrical compartment 3 can be a battery compartment for accommodating the battery.
  • the circuit board 4 is mounted below the navigation antenna 2.
  • the circuit board 4 is disposed parallel to the plane formed by the roll axis and the pitch axis of the movable device.
  • the navigation antenna 2 is a passive antenna, and the passive antenna is integrally provided with the receiver 4 of the movable device.
  • the outer cover 11 and the lower cover 12 of the outer casing of the body 1 are in a state of being engaged.
  • FIG. 1B and FIG. 3B the state in which the upper cover 11 and the lower cover 12 of the outer casing of the body 1 are separated from each other will be described below.
  • FIG. 1B is an exploded view of FIG. 1A.
  • 3B is an exploded view of FIG. 3A.
  • the navigation antenna 2 when the navigation antenna 2 is a passive antenna, it is integrated with the circuit board 4. design.
  • the circuit board 4 is, for example, a Global Navigation Satellite System (GNSS) receiver.
  • GNSS Global Navigation Satellite System
  • the navigation antenna 2 may be an active antenna in addition to the passive antenna.
  • FIG. 6A is a schematic structural view of Embodiment 4 of the movable device of the present invention
  • FIG. 6B is an exploded view of FIG. 6A.
  • the navigation antenna 2 when the navigation antenna 2 is an active antenna, it is separately designed from the circuit board 4 and connected by a radio frequency cable 5 or the like.
  • the antenna efficiency of a navigation antenna is usually measured by four important parameters such as gain (Gain), standing wave (VSWR), noise figure (Noise figure), and axial ratio (Axial ratio).
  • Gain gain
  • VSWR standing wave
  • Noise figure noise figure
  • axial ratio axial ratio
  • the lobe gain of the GPS antenna and the GLONASS antenna is attenuated in the tail direction of the movable device, as shown in the figure between 270 degrees and 360 degrees (0 degrees), the lobe gain The attenuation is such that the lobe gain curve between 0 degrees and 90 degrees is extremely asymmetrical with the lobe gain curve between 270 degrees and 360 degrees (0 degrees).
  • FIG. 7B when the navigation antenna is tilted, the lobe gains of the GPS antenna and the GLONASS antenna are compensated in the tail direction of the movable device, so that the lobe gain curve between 0 degrees and 90 degrees is 270 degrees.
  • the lobe gain curve between ⁇ 360 degrees (0 degrees) is substantially symmetrical.
  • the foregoing program may be stored in a computer readable storage medium, and the program is executed when executed.
  • the foregoing steps include the steps of the foregoing method embodiments; and the foregoing storage medium includes: a medium that can store program codes, such as a ROM, a RAM, a magnetic disk, or an optical disk.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Abstract

一种可移动装置，包括机身（1）以及倾斜设置在机身（1）的边缘部位的导航天线（2）。该导航天线（2）靠近机身（1）的中心部的一侧的高度大于导航天线（2）远离机身（1）的中心部的另外一侧。这种装置能够弥补不规则的机身（1）对导航天线（2）的引向作用，保证天线效率同时改善方向图。

Description

可移动装置 技术领域
本发明涉及飞行器技术领域，尤其涉及一种可移动装置。
背景技术
导航天线是可移动装置的重要组件，一般会水平安装在可移动装置几何中心的顶部，用于接收卫星发送的无线电信号，并由接收机对无线电信号进行转换。
一般来说，由于工业设计的要求，由可移动装置的金属外形充当导航天线的反射面。然而，随着技术的不断发展，可移动装置的外观呈现多元化趋势，导航天线与可移动装置共形，以避免对可移动装置的飞行产生额外的气动阻力。此时，无法保证导航天线被安装在可移动装置的几何中心顶部，而非规则形状的可移动装置的金属外形对导航天线的方向图起到引向作用，从而使得导航天线的方向图发生改变。为避免导航天线的方向图发生改变，传统方法通过更改导航天线的形状，并重新评估导航天线的各类参数，从而减少方向图的改变。
上述阻止方向图改变的过程中，是通过更改导航天线的形状实现的。然而，对导航天线的形状进行更改，势必会导致导航天线的天线效率发生变化，无法达到保证天线效率的同时，改善方向图的目的。
发明内容
本发明实施例提供一种可移动装置，通过将导航天线倾斜设置在可移动装置的边缘部位，实现保证天线效率的同时改善方向图的目的。
一方面，本发明实施例提供一种可移动装置，包括机身；以及导航天线，设置于所述机身的边缘部位；其中，所述导航天线相较于所述机身倾斜设置，使所述导航天线靠近所述机身的中心部的一侧的高度大于所述导航天线远离所述机身的中心部的另外一侧。
本发明实施例提供的可移动装置，其包括机身以及倾斜设置在机身的边 缘部位的导航天线，该导航天线靠近机身的中心部的一侧的高度大于导航天线远离机身的中心部的另外一侧。此时，因为机身呈现容性引向作用，导航天线的方向图会向靠近机身的中心部的方向偏移，而导航天线的倾斜方向为远离机身的中心部的方向，使导航天线倾斜的角度与天线方向图偏移角度相反，因此可以弥补不规则的机身对导航天线的引向作用，实现保证天线效率的同时改善方向图的目的。
附图说明
为了更清楚地说明本发明方法实施例的技术方案，下面将对实施例描述中所需要使用的附图作一简单地介绍，显而易见地，下面描述中的附图是本发明方法的一些实施例，对于本领域技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1A为本发明可移动装置实施例一的结构示意图；
图1B为图1A的分解图；
图2A为外形规则的可移动装置的导航天线水平设置时导航天线的方向图的示意图；
图2B为非规则外形的可移动装置的导航天线水平设置时导航天线的方向图的示意图；
图2C为非规则外形的可移动装置的导航天线倾斜设置时导航天线的方向示意图；
图3A为本发明可移动装置实施例二的结构示意图；
图3B为图3A的分解图；
图4为本发明可移动装置实施例三的结构示意图；
图5为本发明可移动装置所适用的三维坐标图；
图6A为本发明可移动装置实施例四的结构示意图；
图6B为图6A的分解图；
图7A为导航天线未倾斜设置时波瓣增益仿真图；
图7B为导航天线倾斜设置时波瓣增益仿真图。
具体实施方式
为使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。以下内容为结合附图及较佳实施例，对依据本发明申请的具体实施方式、结构、特征及其功效的详细说明。
本发明的说明书和权利要求书及上述附图中的术语“第一”、“第二”、“第三”、“第四”等(如果存在)是用于区别类似的对象，而不必用于描述特定的顺序或先后次序。应该理解这样使用的数据在适当情况下可以互换，以便这里描述的本发明的实施例例如能够以除了在这里图示或描述的那些以外的顺序实施。此外，术语“包括”和“具有”以及他们的任何变形，意图在于覆盖不排他的包含，例如，包含了一系列步骤或单元的过程、方法、系统、产品或设备不必限于清楚地列出的那些步骤或单元，而是可包括没有清楚地列出的或对于这些过程、方法、产品或设备固有的其它步骤或单元。
通常情况下，因无人飞行器的工业设计需要，在满足无人飞行器的美观要求下，导航天线一般作为内置天线，设置在可移动装置壳体内部的中部位置，最好是水平面的中心位置。例如，可移动装置的壳体呈规则的长方体，导航天线水平安装在可移动装置几何中心的顶部，平行于俯仰轴和横滚轴形成的平面。
随着技术的不断发展，可移动装置的外观呈现多元化趋势。此时，受到可移动装置形状的影响，无法保证导航天线被安装在可移动装置的几何中心顶部。由于非规则形状的可移动装置的金属外形的反射面作用削弱，而对导航天线的方向图起到引向作用增强，从而使得导航天线的方向图发生偏移。为避免导航天线的方向图发生偏移，传统方法通过更改导航天线的形状，并重新评估导航天线的各类参数，从而减少方向图的改变。
由于导航天线的天线效率与导航天线的投影面积相关，投影面积越大，天线效率越高。若对导航天线的形状进行更改，则导致导航天线的投影面积发生改变，进而导致导航天线的天线效率发生变化，无法达到保证天线效率 的同时，改善方向图的目的。
有鉴于此，本发明实施例提供一种可移动装置，通过将导航天线倾斜设置在可移动装置的边缘部位，实现保证天线效率的同时改善方向图的目的。
本实施例提供的可移动装置具体可以为无人飞行器、无人车、无人船等。本实施例以可移动装置为无人飞行器为例，特别是多旋翼无人飞行器，进行详细说明。
图1A为本发明可移动装置实施例一的结构示意图。如图1A所示，本实施例提供的可移动装置包括：机身1、以及导航天线2。导航天线2安装于所述机身1的边缘部位；其中，所述导航天线2相较于所述机身1倾斜设置，使所述导航天线2靠近所述机身1的中心部的一侧的高度大于所述导航天线2远离所述机身1的中心部的另外一侧。
具体的，本发明实施例中，用于接收无线电信号的导航天线2与机身1共形设置，该导航天线2安装在机身1内部的边缘部位，且相较于机身1倾斜设置，倾斜的方向与导航天线2的方向图的偏移角度相反，具体实现时可以使导航天线2靠近机身1的中心部的一侧的高度大于导航天线2远离机身1的中心部的另外一侧。此时，因为机身1呈现容性引向作用，导航天线2的方向图会向靠近机身1的中心部的方向偏移，而导航天线2的倾斜方向为远离机身2的中心部的方向，使导航天线2倾斜的角度与天线方向图偏移角度相反，以弥补机身1的引向效果。具体的，可参见图2A、图2B与图2C，图2A为外形规则的可移动装置的导航天线水平设置时导航天线的方向图的示意图，图2B为非规则外形的可移动装置的导航天线水平设置时导航天线的方向图的示意图，图2C为非规则外形的可移动装置的导航天线倾斜设置时导航天线的方向示意图。
请参照图2A，当可移动装置为外形规则的可移动装置时，导航天线设置在可移动装置几何中心的顶部，平行于俯仰轴和横滚轴形成的平面，即图中所示的机身地平面。此时，方向图未发生偏移。
请参照图2B，当可移动装置为外形不规则的可移动装置时，导航天线设置在可移动装置的端部，例如，头部和/或尾部。此时，由于非规则形状的机身1的引向作用，导致方向图发生偏移。如图中，方向图向左偏移，即垂直虚线左侧的方向图的半径大于右侧方向图的半径。
请参照图2C，为了弥补机身1的引向效果，本发明实施例中，将导航天线倾斜设置，倾斜角度与图2B中方向图的偏移方向相反，即向右偏移，具体可提高导航天线的2的靠近机身1的中心部的左侧，使得导航天线的2靠近机身1的中心部的左侧的高度大于导航天线2远离机身1的中心部的右侧的高度。倾斜设置导航天线2后，导航天线2的方向图不再发生偏移，恢复到图2A中的状态。
本发明实施例提供的可移动装置，包括机身1以及倾斜设置在机身1的边缘部位的导航天线2，该导航天线2靠近机身1的中心部的一侧的高度大于导航天线2远离机身1的中心部的另外一侧。此时，因为机身1呈现容性引向作用，导航天线2的方向图会向靠近机身1的中心部的方向偏移，而导航天线2的倾斜方向为远离机身2的中心部的方向，使导航天线2倾斜的角度与天线方向图偏移角度相反，因此可以弥补不规则的机身1对导航天线2的引向作用，实现保证天线效率的同时改善方向图的目的。
可选的，在本发明一实施例中，导航天线2具体设置在机身1的端部。例如，设置在可移动装置的头部；再如，设置在可移动装置的尾部；又如，在可移动装置的头部和尾部均设置导航天线2。
具体的，可移动装置的中部容置有电池等具有辐射作用的元件，若将可移动装置的中部作为可移动装置的几何中心，则电池等元件占用原本用于设置导航天线2的位置。本发明实施中，将导航天线2灵活的设置在机身1的头部或尾部，或头部与尾部均设置导航天线2，可以实现导航天线2与电池等辐射元件和平共存的目的。具体的，可参见图1A、图3A与图4。图3A为本发明可移动装置实施例二的结构示意图，图4为本发明可移动装置实施例三的结构示意图。其中，图1A中，导航天线2设置在可移动装置的尾部，图3A中，导航天线2设置在可移动装置的头部，图4中，导航天线2设置在可移动装置的头部与尾部。
请参照图4，当在可移动装置的头部和尾部均设置导航天线2时，导航天线2包括第一导航天线21和第二导航天线22，第一导航天线21设置在可移动装置的头部，第二导航天线22设置在可移动装置的尾部。
进一步的，当可移动装置前进飞行时，第一导航天线21工作；当可移动装置后退飞行时，第二导航天线22工作。
然而，本发明并不以此为限制，在其他可行的实现方式中，第一导航天线21和第二导航天线22也可以同时工作，例如，当第一导航天线21和第二导航天线均为实时动态测量(Real Time Kinematic，RTK)天线时，第一导航天线21与第二导航天线22同时工作。或者，第一导航天线21与第二导航天线22也可以相互切换。例如，可移动装置前进飞行时，第一导航天线21工作，若第一导航天线21的信号较弱，则可以切换到第二导航天线22，由第二导航天线22接收无线电信号。
可选的，在本发明一实施例中，导航天线2相对于所述机身1倾斜的预设角度，随所述导航天线2距离所述机身1的中心部的距离的增大而增大。例如，再请参照图4，中间的虚线为可移动装置的中心线，第一导航天线21与机身1的中心部的距离为距离1，第一导航天线22相对于俯仰轴和横滚轴形成的平面(如图4中横向的虚线所示)的预设倾斜角为α，第二导航天线22与机身1的中心部的距离为距离2，第二导航天线22相对于俯仰轴和横滚轴形成的平面的预设倾斜角为β。由于距离1小于距离2，因此，第一导航天线21相对于机身1倾斜的预设角度，小于第二导航天线22相对于机身1倾斜的预设角度，即α＜β。
可选的，在本发明一实施例中，导航天线2设置在机身1的侧边位置，从而使得导航天线2的设置位置不局限与可移动装置的头部或尾部，实现导航天线2的灵活设置。
图5为本发明可移动装置所适用的三维坐标图，其中，X轴、Y轴、Z轴分别为俯仰轴、横滚轴与偏航轴。
请参照图5，可选的，在本发明一实施例中，导航天线2相较于机身1倾斜设置，具体在图示的实施例中，导航天线2相较于可移动装置的横滚轴与俯仰轴形成的平面倾斜预设角度，该预设角度介于1度～60度之间，例如，导航天线2倾斜5°、10°、12°、15°、18°、25°、28°、30°、35°38°、42°、46°、49°、50°、53°、55°、58°、60°。作为优选，当导航天线2相较于可移动装置的横滚轴与俯仰轴形成的平面倾斜预设角度时，该倾斜角度介于30度～50度之间，例如，30°、33°、35°、37°、38.5°、40°、45°、50°。
再请参照图5，可选的，在本发明一实施例中，导航天线2相较于机身1 倾斜设置，具体在图示的实施例中，导航天线2相较于所述可移动装置的偏航轴预设角度。该预设角度介于1度～60度之间，例如，30°、32°、35°、38°、40°、42°、46°、48.6°、50°、52°、57°、60°、64°、67°、69°、70°、72°、74.7°、76°、79°、80°、83°、85.2°、86°、88°、89°。作为优选，当导航天线2相较于所述可移动装置的偏航轴预设角度，该角度介于40度～60度之间，例如40°、45°、50°、53°、55°、58°、60°。
再请参照图5，可选的，在本发明一实施例中，导航天线2相较于机身1倾斜设置，具体在图示的实施例中，导航天线2平行于所述可移动装置的偏航轴设置，即导航天线2基本平行于可移动装置的俯仰轴或完全平行于可移动装置的偏航轴设置。
本发明实施例中，从天线极化的角度来讲，导航天线2可以为右旋天线等；从频段的角度来讲，上述的导航天线2为全球定位系统(Global Positioning System，GPS)天线或格洛纳斯(GLONASS)天线、Wi-Fi天线等。当导航天线2为GPS天线时，其例如为右旋圆极化(Right Hand Circular Polarizaition，RHCP)，从而使得导航天线2顺利接收无线电信号。
可选的，在本发明一实施例中，机身1包括外壳体以及电气仓，所述电气仓设置于所述外壳体的顶面中部，所述导航天线2设置在所述外壳体内。
具体的，再请参见图1A，机身1的外壳体包括对合设置的上盖11与下盖12，对合设置的上盖与下盖对合后形成容纳空间，电气仓3位于容纳空间的顶面中部，导航天线2位于容纳空间内的边缘部位，如容纳空间内的头部和/或尾部。其中，在图示的实施中，电气仓3可以为电池仓，用于容置电池。
可选的，在本发明一实施例中，导航天线2的下方安装电路板4。该电路板4平行于可移动装置的横滚轴和俯仰轴形成的平面设置。
上述图1A、图3A与图4实施例中，导航天线2为无源天线，该无源天线与可移动装置的接收机4一体化设置。其中，图1A、图3A与图4中，机身1的外壳体包括的上盖11与下盖12处于对合状态。为清楚起见，下面将示出机身1的外壳体包括的上盖11与下盖12分离的状态图，具体的，可参见图1B、与图3B，图1B为图1A的分解图，图3B为图3A的分解图。
请参照图1B与图3B，当导航天线2为无源天线时，其与电路板4一体 设计。其中，电路板4例如为全球导航卫星系统(Global Navigation Satellite System，GNSS)接收机。
另外，本发明实施例中，导航天线2除了为无源天线外，还可以是有源天线。具体的，可参见图6A与图6B，图6A为本发明可移动装置实施例四的结构示意图，图6B为图6A的分解图。
请参照图6A与图6B，当导航天线2为有源天线时，其与电路板4分立设计，并通过射频电缆5等连接。
导航天线的天线效率通常通过四个重要参数，如增益(Gain)、驻波(VSWR)、噪声系数(Noise figure)、轴比(Axial ratio)等进行衡量。下面，从增益的角度，对本发明实施例的可移动装置保证天线效率的同时改善方向图的效果进行详细说明。具体的，可参见图7A与图7B，图7A为导航天线未倾斜设置时波瓣增益仿真图，图7B为导航天线倾斜设置时波瓣增益仿真图。
请参照图7A，当导航天线水平设置时，GPS天线和GLONASS天线的波瓣增益在可移动装置的尾部方向均会衰减，如图中270度～360度(0度)之间，波瓣增益衰减，使得0度～90度之间的波瓣增益曲线，与270度～360度(0度)之间的波瓣增益曲线极度不对称。而图7B中，当导航天线倾斜设置时，GPS天线和GLONASS天线的波瓣增益在可移动装置的尾部方向均得到了补偿，使得0度～90度之间的波瓣增益曲线，与270度～360度(0度)之间的波瓣增益曲线基本对称。
本领域普通技术人员可以理解：实现上述方法实施例的全部或部分步骤可以通过程序指令相关的硬件来完成，前述的程序可以存储于一计算机可读取存储介质中，该程序在执行时，执行包括上述方法实施例的步骤；而前述的存储介质包括：ROM、RAM、磁碟或者光盘等各种可以存储程序代码的介质。
最后应说明的是：以上各实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述各实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例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各实施例技术方案的范围。

Claims (21)

  1. 一种可移动装置，其特征在于，包括：
    机身；以及
    导航天线，设置于所述机身的边缘部位；
    其中，所述导航天线相较于所述机身倾斜设置，使所述导航天线靠近所述机身的中心部的一侧的高度大于所述导航天线远离所述机身的中心部的另外一侧。
  2. 根据权利要求1所述的可移动装置，其特征在于，
    所述导航天线设置在所述机身的端部。
  3. 根据权利要求2所述的可移动装置，其特征在于，
    所述端部包括所述可移动装置的头部和/或尾部；
    相应的，所述导航天线包括第一导航天线和/或第二导航天线，所述第一导航天线设置在所述可移动装置的头部，所述第二导航天线设置在所述可移动装置的尾部。
  4. 根据权利要求3所述的可移动装置，其特征在于，
    所述可移动装置前进飞行时，所述第一导航天线工作；
    所述可移动装置后退飞行时，所述第二导航天线工作。
  5. 根据权利要求1所述的可移动装置，其特征在于，所述导航天线设置在所述机身的侧边位置。
  6. 根据权利要求1～5任一项所述的可移动装置，其特征在于，
    所述导航天线相对于所述机身倾斜的预设角度，随所述导航天线距离所述机身的中心部的距离的增大而增大。
  7. 根据权利要求1～5任一项所述的可移动装置，其特征在于，
    所述导航天线相较于所述可移动装置的横滚轴与俯仰轴形成的平面倾斜预设角度。
  8. 根据权利要求7所述的可移动装置，其特征在于，
    所述预设角度介于1度～60度之间。
  9. 根据权利要求8所述的可移动装置，其特征在于，
    所述预设角度介于10度～45度之间。
  10. 根据权利要求1～5任一项所述的可移动装置，其特征在于，
    所述导航天线相较于所述可移动装置的偏航轴预设角度。
  11. 根据权利要求10所述的可移动装置，其特征在于，
    所述预设角度介于30度～89度之间。
  12. 根据权利要求11所述的可移动装置，其特征在于，
    所述预设角度介于40度～60度之间。
  13. 根据权利要求1～5任一项所述的可移动装置，其特征在于，
    所述导航天线平行于所述可移动装置的俯仰轴。
  14. 根据权利要求1～5任一项所述的可移动装置，其特征在于，
    所述导航天线为全球定位系统GPS天线或格洛纳斯天线。
  15. 根据权利要求1～5任一项所述的可移动装置，其特征在于，
    所述机身包括外壳体以及电气仓，所述电气仓设置于所述外壳体的顶面中部，所述导航天线设置在所述外壳体内。
  16. 根据权利要求15所述的可移动装置，其特征在于，
    所述电气仓为电池仓，所述电池仓用于容置电池。
  17. 根据权利要求1～5任一项所述的可移动装置，其特征在于，
    所述导航天线的下方安装电路板。
  18. 根据权利要求17所述的可移动装置，其特征在于，
    所述电路板平行于横滚轴与俯仰轴形成的平面设置。
  19. 根据权利要求17所述的可移动装置，其特征在于，
    所述导航天线为无源天线，所述无源天线与所述电路板一体化设计。
  20. 根据权利要求17所述的可移动装置，其特征在于，
    所述导航天线为有源天线，所述有源天线与所述电路板分立设计。
  21. 根据权利要求20所述的可移动装置，其特征在于，
    所述有源天线与所述电路板通过射频电缆连接。
PCT/CN2016/100438 2016-09-27 2016-09-27 可移动装置 Ceased WO2018058329A1 (zh)

Priority Applications (5)

Application Number Priority Date Filing Date Title
CN201680002573.5A CN106797070B (zh) 2016-09-27 2016-09-27 可移动装置
PCT/CN2016/100438 WO2018058329A1 (zh) 2016-09-27 2016-09-27 可移动装置
CN202010121566.5A CN111313142B (zh) 2016-09-27 2016-09-27 可移动装置及无人飞行器
US16/365,971 US11171413B2 (en) 2016-09-27 2019-03-27 Movable device
US17/490,560 US20220021106A1 (en) 2016-09-27 2021-09-30 Movable device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/100438 WO2018058329A1 (zh) 2016-09-27 2016-09-27 可移动装置

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US16/365,971 Continuation US11171413B2 (en) 2016-09-27 2019-03-27 Movable device

Publications (1)

Publication Number Publication Date
WO2018058329A1 true WO2018058329A1 (zh) 2018-04-05

Family

ID=58952318

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/100438 Ceased WO2018058329A1 (zh) 2016-09-27 2016-09-27 可移动装置

Country Status (3)

Country Link
US (2) US11171413B2 (zh)
CN (2) CN111313142B (zh)
WO (1) WO2018058329A1 (zh)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201163658Y (zh) * 2008-03-03 2008-12-10 苑洪祥 仿真航模飞机天线装置
US20140306851A1 (en) * 2013-04-11 2014-10-16 Raytheon Company Integrated antenna and antenna component
CN204315727U (zh) * 2014-12-31 2015-05-06 河北科技大学 一种无人机导航天线
CN105281016A (zh) * 2015-11-06 2016-01-27 北京航空航天大学 一种无人机机载天线布局设计及验证方法
CN205029006U (zh) * 2015-10-23 2016-02-10 成都九华圆通科技发展有限公司 一种用于监测测向的飞行器
CN105818961A (zh) * 2016-05-13 2016-08-03 黄剑锋 一种多天线机身融合无人机

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07106821A (ja) * 1993-09-30 1995-04-21 Japan Radio Co Ltd 円偏波マイクロストリップアンテナ
EP0884796A3 (en) * 1997-06-11 1999-03-24 Matsushita Electric Industrial Co., Ltd. Antenna device consisting of bent or curved portions of linear conductor
US6266582B1 (en) * 1997-08-06 2001-07-24 Rockwell Collins. Inc. GPS analytic redundancy for gyroscope failure detection
CA2496053A1 (en) * 2002-08-20 2004-03-04 Aerosat Corporation Communication system with broadband antenna
US9493235B2 (en) * 2002-10-01 2016-11-15 Dylan T X Zhou Amphibious vertical takeoff and landing unmanned device
CN1979946A (zh) * 2005-12-02 2007-06-13 马冠一 可用于多方位收发信与动态载体的微带天线阵系统
EP1808710A1 (en) * 2006-01-11 2007-07-18 International University Bremen Gmbh Method and device for determining the speed of a moving entity
US8145391B2 (en) * 2007-09-12 2012-03-27 Topcon Positioning Systems, Inc. Automatic blade control system with integrated global navigation satellite system and inertial sensors
GB2468345B (en) * 2009-03-05 2014-01-15 Cranfield Aerospace Ltd Unmanned air vehicle (uav) control system and method
IL199230A0 (en) * 2009-06-08 2011-07-31 Elta Systems Ltd Air vehicle
CN201616506U (zh) * 2010-03-26 2010-10-27 华为终端有限公司 移动通信天线设备及移动通信终端设备
US20140197280A1 (en) * 2011-11-22 2014-07-17 Donald Earl Smith Delta Wing Unmanned Aerial Vehicle (UAV) and Method of Manufacture of the Same
US20160376000A1 (en) * 2014-07-10 2016-12-29 Christoph Kohstall Submersible unmanned aerial vehicles and associated systems and methods
US20160059827A1 (en) * 2014-08-27 2016-03-03 Lear Corporation Optimizing uwb satellite antenna in-vehicle positioning
EP3240726B1 (en) * 2015-01-03 2020-08-05 Joseph B. Seale Rotary wing vtol with fixed wing forward flight mode
CN105356039A (zh) * 2015-11-19 2016-02-24 江西洪都航空工业集团有限责任公司 一种卫星导航与通信天线一体化布置结构
CN105823478A (zh) * 2016-03-14 2016-08-03 武汉卓拔科技有限公司 一种自主避障导航信息共享和使用方法
CN105652289B (zh) * 2016-03-24 2017-12-08 北京空间飞行器总体设计部 一种全空间可见的星载gps接收系统
CN205561808U (zh) * 2016-04-22 2016-09-07 徐州斯塬农科网络科技有限公司 北斗定位的农机耕深监测终端
US9980267B2 (en) * 2016-05-06 2018-05-22 Bridgewest Finance Llc Unmanned aerial vehicle (UAV) beam pointing and data rate optimization for high throughput broadband access
CN105857182A (zh) * 2016-05-19 2016-08-17 奇瑞汽车股份有限公司 一种电动汽车
US11014666B2 (en) * 2016-09-23 2021-05-25 Skydio, Inc. Airframe
CN212541105U (zh) * 2020-05-27 2021-02-12 江苏东方恒基通用航空有限公司 适用于无人机远距离遥控的装置

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201163658Y (zh) * 2008-03-03 2008-12-10 苑洪祥 仿真航模飞机天线装置
US20140306851A1 (en) * 2013-04-11 2014-10-16 Raytheon Company Integrated antenna and antenna component
CN204315727U (zh) * 2014-12-31 2015-05-06 河北科技大学 一种无人机导航天线
CN205029006U (zh) * 2015-10-23 2016-02-10 成都九华圆通科技发展有限公司 一种用于监测测向的飞行器
CN105281016A (zh) * 2015-11-06 2016-01-27 北京航空航天大学 一种无人机机载天线布局设计及验证方法
CN105818961A (zh) * 2016-05-13 2016-08-03 黄剑锋 一种多天线机身融合无人机

Also Published As

Publication number Publication date
US20220021106A1 (en) 2022-01-20
CN111313142B (zh) 2022-05-27
US20190221924A1 (en) 2019-07-18
US11171413B2 (en) 2021-11-09
CN111313142A (zh) 2020-06-19
CN106797070A (zh) 2017-05-31
CN106797070B (zh) 2020-03-27

Similar Documents

Publication Publication Date Title
US12476353B2 (en) Antenna system mounted in vehicle
US7071879B2 (en) Dielectric-resonator array antenna system
EP3025392B1 (en) Polarization dependent electromagnetic bandgap antenna and related methods
EP3375044B1 (en) Directive fixed beam ramp ebg antenna mounted within a cavity
JP4999098B2 (ja) 複合アンテナ
TW201810203A (zh) 全方向無人飛行載具之控制天線方位定向的系統與裝置
US8144067B2 (en) Combination planar and parabolic reflector antenna to access satellite
US10707564B2 (en) Unmanned aerial vehicle
US8059056B2 (en) Directional antenna and portable electronic device using the same
US6833815B2 (en) Cavity embedded meander line loaded antenna
US10340582B2 (en) Metal frame body and terminal including same
WO2018058329A1 (zh) 可移动装置
CN206076485U (zh) 可移动装置
WO2017094441A1 (ja) 衛星電波受信用アンテナ装置
CN107516762B (zh) 一种天线结构及移动终端
CN112201953B (zh) 卫星通信系统和/或导航系统天线
JP6440300B2 (ja) 広帯域アンテナ
JP7040951B2 (ja) アンテナ装置
US12261357B2 (en) Antenna apparatus for suppressing multipath signals
Park et al. Low-profile ferrite loaded conical antenna
US20250141533A1 (en) Method and devices for providing backhaul links
WO2019085437A1 (zh) 一种无人机的天线结构及无人机
KR20170003990U (ko) 차량용 다이폴 안테나
Wu Low cost L‐band mobile terminal antennas for helicopters
Ilcev Classification and Characteristics of Mobile Satellite Antennas (MSA)

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 16917089

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 16917089

Country of ref document: EP

Kind code of ref document: A1