WO2018090435A1 - 飞行器 - Google Patents

飞行器 Download PDF

Info

Publication number
WO2018090435A1
WO2018090435A1 PCT/CN2016/111920 CN2016111920W WO2018090435A1 WO 2018090435 A1 WO2018090435 A1 WO 2018090435A1 CN 2016111920 W CN2016111920 W CN 2016111920W WO 2018090435 A1 WO2018090435 A1 WO 2018090435A1
Authority
WO
WIPO (PCT)
Prior art keywords
antenna
arm
aircraft
assembly
disposed
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/CN2016/111920
Other languages
English (en)
French (fr)
Inventor
梁贵彬
张永生
王佳迪
陈星元
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 CN201680088323.8A priority Critical patent/CN109562821A/zh
Publication of WO2018090435A1 publication Critical patent/WO2018090435A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • 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
    • 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
    • B64U60/00—Undercarriages
    • B64U60/50—Undercarriages with landing legs

Definitions

  • the invention relates to the field of drones, and more particularly to an aircraft.
  • the aircraft can be used in aerial photography, mapping, plant protection, detection, disaster relief and other industries.
  • the structure usually consists of a central frame, a power system, a landing gear, etc., and is carried out by carrying flight control, image transmission and other microcomputer equipment. .
  • the data acquired during the operation of the aircraft will communicate with ground equipment such as remote control, computer, etc. through the antenna amplification signal.
  • the location of the antenna on the aircraft is different, which will affect the optimal signal point of the antenna, which will affect the overall performance of the aircraft. Therefore, the design layout of the antenna in flight is reasonable and directly affects the performance of the aircraft.
  • the antenna is generally placed on the center frame or the landing gear of the aircraft.
  • the antenna is designed on the center frame, and the equipment on the center frame will affect the performance of the antenna.
  • the antenna is designed on the landing gear, and the antenna is connected with the key design on the center frame, which may result in the landing gear not being designed as a quick release method or the quick release method being too complicated to design and inconvenient to use.
  • the present invention provides an aircraft.
  • an aircraft including a center frame, an antenna, and an arm assembly coupled to the center frame;
  • the arm assembly includes a boom, the antenna being disposed on the arm and away from the center frame.
  • the aircraft further includes a connector disposed on the arm, the connector for fixing the antenna to the arm.
  • the connecting member includes a locking sleeve adapted to the arm, and an antenna holder coupled to the locking sleeve, the antenna seat for carrying the antenna.
  • the antenna mount includes a body portion including an accommodation space for accommodating the antenna.
  • the body portion further includes a wire hole located above the accommodating space.
  • the locking sleeve includes a connecting end connected to the antenna base, and a locking end for fixing the locking sleeve to the arm.
  • a plug hole is disposed in the connecting end, and a wiring hole is disposed on the arm corresponding to the plug hole, and a connecting line of the antenna passes through the plug hole and the wiring hole to enter the arm Inside.
  • an elastic member for sealing the plug hole and the wiring hole may be placed in the plug hole.
  • the antenna is located below the arm.
  • the polarization direction of the antenna is perpendicular to the horizontal plane
  • the polarization direction of the antenna is perpendicular to the extending direction of the arm.
  • the antenna is a dipole antenna.
  • the aircraft further includes a landing gear assembly, the arm assembly being foldably coupled to the center frame; the antenna facing the center of the aircraft when the arm assembly is in a stowed state, the antenna being Located inside the landing gear assembly and the arm assembly.
  • an aircraft including a center frame, an antenna, and an arm assembly coupled to the center frame; the arm assembly is foldably coupled to the center frame;
  • the arm assembly includes a robot arm, the antenna is disposed on the arm, and the antenna faces a center of the aircraft when the arm assembly is in a stowed state, so that the antenna is located at the landing gear The assembly and the inside of the arm assembly.
  • the aircraft further includes a connector disposed on the arm, the connector for fixing the antenna to the arm.
  • the connecting member includes a locking sleeve adapted to the arm, and the locking sleeve A connected antenna mount for carrying the antenna.
  • the antenna mount includes a body portion including an accommodation space for accommodating the antenna.
  • the body portion further includes a wire hole located above the accommodating space.
  • the locking sleeve includes a connecting end connected to the antenna base, and a locking end for fixing the locking sleeve to the arm.
  • a plug hole is disposed in the connecting end, and a wiring hole is disposed on the arm corresponding to the plug hole, and a connecting line of the antenna passes through the plug hole and the wiring hole to enter the arm Inside.
  • an elastic member for sealing the plug hole and the wiring hole may be placed in the plug hole.
  • the antenna is located below the arm; or
  • the polarization direction of the antenna is perpendicular to the horizontal plane
  • the polarization direction of the antenna is perpendicular to the extending direction of the arm.
  • the antenna is a dipole antenna.
  • the technical solution provided by the embodiment of the present invention may include the following effects: the aircraft sets the antenna on the arm, and the setting away from the center frame of the aircraft avoids other components from affecting the performance of the antenna, and ensures that the stand is easily disassembled.
  • FIG. 1 is a schematic view of an aircraft shown in an embodiment of the present invention.
  • FIG. 2 is a schematic view showing the connection between the arm of the aircraft and the connecting member according to an embodiment of the invention.
  • FIG 3 is an exploded view of an arm and a connecting member of an aircraft according to an embodiment of the present invention.
  • FIG. 4 is a schematic view showing the stowed state of an arm assembly of an aircraft according to an embodiment of the present invention.
  • Embodiment 1 is a diagrammatic representation of Embodiment 1:
  • an aircraft 100 shown in this embodiment includes a center frame 1 , an antenna 3 , and an arm assembly 2 connected to the center frame 1 , wherein the center frame 1 is provided with electrical equipment. And metal parts, etc.
  • the arm assembly 2 is foldably or non-foldably connected to the center frame 1.
  • the arm assembly 2 includes a robot arm 21 that is disposed on the arm 21 and away from the center frame 1 .
  • the antenna 3 is disposed on the arm 21 to move the antenna 3 away from electrical equipment, metal parts, and the like in the center frame 1 to avoid interference of signals of the antenna 3, such as electrical equipment and metal parts.
  • the antenna 3 is disposed away from the center frame 1, in the middle of the arm 21 or toward the middle of the arm 21.
  • the present invention provides the antenna 3 of the aircraft 100 on the arm 21 of the arm assembly 2, and the antenna 3 is available at a position away from the center frame 1 without interference from electrical equipment and metal parts. Better performance.
  • the aircraft 100 further includes a connector 4 disposed on the arm 21 for fixing the antenna 3 to the arm 21.
  • the antenna 3 can be directly fixed on the arm 21, for example, the antenna 3 is glued to the arm 21; the antenna can also be connected through a connecting member 4. 3 is fixed to the arm 21.
  • the connecting member 4 includes a locking sleeve 41 adapted to the arm 21 and an antenna holder 42 coupled to the locking sleeve 41.
  • the antenna mount 42 is used to carry the antenna 3.
  • the locking sleeve 41 is detachably or non-detachably connected to the arm 21 .
  • the locking sleeve 41 and the arm 21 are in a snap-fit connection, and the locking sleeve 41 and the arm 21 can also be fixedly connected by bolts or screws.
  • the antenna mount 42 includes a body portion 421, and the body portion 421 includes The accommodating space 423 of the antenna 3 is accommodated. That is, the accommodating space 423 is disposed in the antenna base 42 for carrying the antenna 3.
  • the antenna 3 can also be directly placed in the accommodating space 423, and a baffle 424 is disposed on the body portion 412 for fixing the antenna 3 to the accommodating portion.
  • the baffle 424 can be disposed at an upper portion of the accommodating space 423.
  • the antenna 3 can also be embedded in the accommodating space 423.
  • the body portion 421 further includes a wire hole 422 located above the accommodating space 423, and the wire hole 422 is allowed to pass through the connecting line 31 of the antenna 3.
  • the locking sleeve 41 includes a connecting end 412 connected to the antenna base 42, and a locking end 411 for fixing the locking sleeve 41 to the arm 21.
  • the locking end 411 can fix the locking sleeve 41 to the arm 21 by means of a screw 6.
  • a screw hole is opened in the locking end 411, and the screw 6 is screwed through the screw hole to lock the locking end 411.
  • a plug hole 413 is defined in the connecting end 412, and a wiring hole (not shown) is disposed on the arm 21 corresponding to the plug hole 413.
  • the connecting line 31 of the antenna 3 passes through the plug hole 413 and the wiring hole into the arm 21.
  • the connecting line 31 of the antenna 3 is placed in the arm 21 to protect the connecting line 31 from damage, and the wiring disorder is prevented from affecting the appearance of the aircraft. It is true that in other embodiments, the connecting wire 31 can also be directly attached to the arm 21 or the connecting wire 31 can be fixed to the arm 21 using a fixing member.
  • an elastic member 43 for sealing the plug hole 413 and the wiring hole may be placed in the plug hole 413.
  • the elastic member 43 can be a silicone plug, and the connecting wire 31 of the antenna 3 can pass through the silicone plug. That is, the connecting wire 31 passes through the silicone plug into the arm 21, and the silicone plug is placed in the plug hole 413 and the wiring hole.
  • the silicone plug further protects the connecting line 31.
  • the antenna 3 when the arm 21 is opened, the antenna 3 is located below the arm 21.
  • the number of the antennas 3 is two or more, and is respectively disposed on different arms 21.
  • the polarization direction of the antenna 3 is set to be perpendicular to the horizontal plane, below the arm 21.
  • the antenna 3 is disposed under the arm 21 to ensure that the antenna 3 faces the center of the entire aircraft 100 when the arm assembly 2 is folded and folded, and the outer arm assembly 2 can protect the antenna 3 and make the antenna 3 Free from collisions, etc., which facilitates packaging, handling, and movement.
  • the performance achieved when the polarization direction of the antenna 3 is perpendicular to the horizontal plane is optimal.
  • the extending direction of the antenna 3 overlaps with the polarization direction of the antenna 3. Therefore, in the present embodiment, the extending direction of the antenna 3 provided on the arm 21 is perpendicular to the ground.
  • the antenna 3 when the arm assembly 2 is opened, the antenna 3 can also be located above the arm 21, and when the arm assembly 3 is folded and folded, the antenna 3 is folded or rotated so that It is oriented toward the center of the aircraft 100 to avoid damage to the outside of the arm 21.
  • the polarization direction of the antenna 3 is perpendicular to the extending direction of the arm 21.
  • the arm 21 When the arm 21 is deployed, it is substantially parallel to the horizontal plane, so that the angle between the antenna 3 and the horizontal plane disposed on the arm 21 and perpendicular to the arm 21 is also close to ninety degrees.
  • the polarization direction of the antenna 3 is perpendicular to the extending direction of the arm 21, and it is easy to align when the antenna 3 is mounted, and the appearance of the aircraft 100 is also beautified. It is true that when the arm assembly 2 and the center frame 1 are non-foldable, the angle between the polarization direction of the antenna 3 and the horizontal plane is also close to ninety degrees, which also has the above effects.
  • the extending direction of the antenna 3 overlaps with the polarization direction of the antenna 3. Therefore, in the present embodiment, the extending direction of the antenna 3 is perpendicular to the arm 21 .
  • the aircraft 100 further includes a landing gear assembly 5, and the arm assembly 2 of the aircraft 100 is foldably coupled to the center frame 1.
  • the antenna 3 is located inside the landing gear assembly 5 and the arm assembly 2, and the landing gear assembly 5 and the arm assembly 2 can protect the antenna 3 and prevent the antenna 3 from being subjected to damage. That is, the arm assembly 2 is foldably connected to the center frame 1, and when the arm assembly 2 is in the stowed state, the antenna 3 faces the center of the aircraft 100, so that the antenna 3 is located The drop frame assembly 5 and the inside of the arm assembly 2 are protected to protect the antenna 3 from damage.
  • the antenna is a dipole antenna, and may also be, for example, an IFA (Inverted F-shaped Antenna), a PIFA (Planar Inverted F-shaped Antenna), a loop antenna, Slot antennas, etc.
  • the loop antenna is a metal guide
  • the wire is wound into a certain shape, such as a circle, a square, a triangle, etc., with the ends of the conductor as the output end.
  • the aircraft 100 is a multi-rotor aircraft 100, including one of a quadrotor aircraft, a six-rotor aircraft, or an eight-rotor aircraft.
  • Embodiment 2 is a diagrammatic representation of Embodiment 1:
  • the present invention provides a further description of an aircraft 100 by another embodiment.
  • the aircraft 100 includes a center frame 1, an antenna 3, and a boom assembly 2 connected to the center frame 1.
  • the arm assembly 2 is foldably connected to the center frame 1.
  • the arm assembly 2 includes a robot arm 21, and the antenna 3 is disposed on the arm 21, and when the arm assembly 2 is in a stowed state, the antenna faces the center of the aircraft, so that the antenna 3 is located inside the landing gear assembly 5 and the arm assembly 2.
  • the arm assembly 2 of the aircraft 100 can be opened or stowed relative to the center frame 1, and the antenna 3 is disposed on the arm 21, and the antenna 3 can be retracted with the arm 21, and
  • the antenna 3 is located inside the landing gear assembly 5 and the arm assembly 2 when the arm assembly 2 is in the stowed state. Since the outer side of the antenna 3 has the landing gear assembly 5 and the arm assembly 2, the landing gear assembly 5 and the arm assembly 2 can protect the antenna 3 when transporting or packaging the aircraft 100. The antenna 3 is protected from collision or the like, and the damage of the external force to the antenna 3 is reduced. Since the antenna 3 is disposed on the arm 21, the landing gear assembly can be designed as a quick release structure, which further reduces the packaging volume of the aircraft and is more advantageous for mobile handling.
  • the antenna 3 when the arm 21 is opened, the antenna 3 is located below the arm 21, and when the arm assembly 2 is in the stowed state, the antenna 3 faces the center or orientation of the aircraft. It tends to the center of the aircraft.
  • the outer arm assembly 2 protects the antenna 3 and protects the antenna 3 from collisions and the like, thereby facilitating packaging, handling, and movement.
  • the polarization direction of the antenna 3 is set to be perpendicular to the horizontal plane, and the achieved performance of the antenna 3 is optimal at this time. It can be understood that when the arm assembly 2 is opened, the antenna 3 can also be located above the arm 21, and when the arm assembly 3 is folded and folded, the antenna 3 is folded or rotated so that It is oriented toward the center of the aircraft 100 to avoid damage to the outside of the arm 21.
  • the polarization direction of the antenna 3 is perpendicular to the direction in which the arm 21 extends.
  • the performance achieved by the antenna 3 is optimal. Therefore, the arrangement of the antenna 3 in the present embodiment optimizes the performance of the antenna 3 while protecting the antenna 3.
  • the arm 21 When the arm 21 is deployed, it is substantially parallel to the horizontal plane, so that the angle between the antenna 3 and the horizontal plane disposed on the arm 21 and perpendicular to the arm 21 is also close to ninety degrees.
  • the polarization direction of the antenna 3 is perpendicular to the extending direction of the arm 21, and it is easy to align when the antenna 3 is mounted, and the appearance of the aircraft 100 is also beautified.
  • the aircraft 100 in this embodiment further includes the following technical features.
  • the technical features described below are the same as or similar to those in the previous embodiment, and the technical effects obtained are the same or similar, and belong to the same inventive concept. Only the relationship between the technical features and technical features of the aircraft 100 will be described below, and the effects between the specific effects or technical features will not be described. For details, refer to the description of the embodiment of the aircraft 100.
  • the aircraft 100 further includes:
  • a connector 4 is provided on the arm 21 for fixing the antenna 3 to the arm 21.
  • the connecting member 4 includes a locking sleeve 41 adapted to the arm 21 and an antenna holder 42 connected to the locking sleeve 41 for carrying the antenna 3.
  • the antenna holder 42 includes a body portion 421 including an accommodation space 423 for accommodating the antenna 3.
  • the body portion 421 further includes a wire hole 422 located above the accommodating space 423.
  • the locking sleeve 41 includes a connecting end 412 connected to the antenna base 42 and a locking end 411 for fixing the locking sleeve 41 to the arm 21 .
  • a plug hole 413 is disposed in the connecting end 412, and a wire hole is disposed on the arm 21 corresponding to the plug hole 413.
  • the connecting wire 31 of the antenna 3 passes through the plug hole 413 and the wiring hole. Inside the arm 21 .
  • An elastic member 43 for sealing the plug hole 413 and the wiring hole may be placed in the plug hole 413.
  • the antenna is a dipole antenna.
  • the aircraft 100 is a multi-rotor aircraft 100, including one of a quadrotor aircraft, a six-rotor aircraft, or an eight-rotor aircraft.
  • the aircraft 100 has the antenna 3 disposed on the arm 21, which solves the interference problem and can obtain a more performance effect than the antenna 3 is disposed on the center frame 1.
  • the antenna is placed under the arm to avoid antenna damage when applied to an aircraft that is capable of folding the arm assembly.
  • Some aircraft with the retractable landing gear assembly 5, using the antenna 3 design on the arm 21, can design the retractable landing gear assembly as a quick-release structure, which can further reduce the packaging volume of the aircraft and facilitate the movement. Handling.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Details Of Aerials (AREA)

Abstract

一种飞行器（100），包括中心架（1）、天线（3），及与所述中心架连接的机臂组件（2），所述机臂组件包括机臂（21）。所述天线设置于所述机臂上且远离所述中心架的位置。该飞行器还包括设置在所述机臂上的连接件（4），所述连接件用于将所述天线固定在所述机臂上。所述飞行器将天线设置在机臂上，远离飞行器中心架设置避免了其他部件影响该天线性能，且可方便脚架的拆卸。

Description

飞行器 技术领域
本发明涉及无人机领域，尤其是一种飞行器。
背景技术
现有技术中，飞行器可用于航拍、测绘、植保、侦测、救灾等行业，其结构上通常有中心架、动力系统、起落架等组成，通过搭载飞控、图传和其他微电脑设备进行作业。
其中，飞行器作业过程中所获取到的数据，会通过天线放大信号与地面设备如遥控器、电脑等进行通讯。而天线在飞行器上的位置布局点不同，会影响天线的最佳信号点，进而影响飞行器的整体性能发挥。因此，天线在飞行上的设计布局是否合理，直接影响飞行器的性能。
多旋翼飞行器由于体积较大，一般将天线设置在飞行器的中心架或者起落架上面。将天线设计在中心架上，中心架上的设备较多会影响天线的性能。将天线设计在起落架上，天线与中心架上的关键设计有连线，会导致起落架不能设计成快拆方式或者快拆方式设计得太复杂，使用不方便。
发明内容
本发明提供一种飞行器。
根据本发明实施例的第一方面，提供一种飞行器，包括中心架、天线，及与所述中心架连接的机臂组件；
所述机臂组件包括机臂，所述天线设置于所述机臂上且远离所述中心架的位置。
所述的飞行器，还包括设置在所述机臂上的连接件，所述连接件用于将所述天线固定在所述机臂上。
进一步地，所述连接件包括与所述机臂适配的锁紧套，及与所述锁紧套连接的天线座，所述天线座用于承载所述天线。
进一步地，所述天线座包括本体部，所述本体部包括用于容纳所述天线的容置空间。
进一步地，所述本体部还包括位于所述容置空间上方的过线孔。
进一步地，所述锁紧套包括与所述天线座连接的连接端，及用于将所述锁紧套固定在所述机臂上的锁紧端。
进一步地，所述连接端内设有塞孔，所述机臂上对应所述塞孔设有布线孔，所述天线的连接线穿过所述塞孔和所述布线孔进入所述机臂内。
进一步地，所述塞孔内可放置用于密封所述塞孔和所述布线孔的弹性件。
进一步地，所述机臂打开时，所述天线位于所述机臂的下方；或者
所述机臂打开时，所述天线的极化方向与水平面垂直；或者
所述天线的极化方向与所述机臂的延伸方向垂直。
进一步地，所述天线为偶极子天线。
进一步地，所述飞行器还包括起落架组件，所述机臂组件与所述中心架可折叠连接；当所述机臂组件处于收起状态时所述天线朝向所述飞行器中心，使所述天线位于所述起落架组件和所述机臂组件内侧。
根据本发明实施例的第二方面，提供一种飞行器，包括中心架、天线及与所述中心架连接的机臂组件；所述机臂组件与所述中心架可折叠连接；
所述机臂组件包括机臂，所述天线设置于所述机臂上，且当所述机臂组件处于收起状态时所述天线朝向所述飞行器中心，使所述天线位于所述起落架组件和所述机臂组件内侧。
所述的飞行器，还包括设置在所述机臂上的连接件，所述连接件用于将所述天线固定在所述机臂上。
进一步地，所述连接件包括与所述机臂适配的锁紧套，及与所述锁紧套 连接的天线座，所述天线座用于承载所述天线。
进一步地，所述天线座包括本体部，所述本体部包括用于容纳所述天线的容置空间。
进一步地，所述本体部还包括位于所述容置空间上方的过线孔。
进一步地，所述锁紧套包括与所述天线座连接的连接端，及用于将所述锁紧套固定在所述机臂上的锁紧端。
进一步地，所述连接端内设有塞孔，所述机臂上对应所述塞孔设有布线孔，所述天线的连接线穿过所述塞孔和所述布线孔进入所述机臂内。
进一步地，所述塞孔内可放置用于密封所述塞孔和所述布线孔的弹性件。
进一步地，所述天线位于所述机臂的下方；或者
所述机臂打开时，所述天线的极化方向与水平面垂直；或者
所述天线的极化方向与所述机臂的延伸方向垂直。
进一步地，所述天线为偶极子天线。
本发明的实施例提供的技术方案可以包括以下有益效果：所述飞行器将天线设置在机臂上，远离飞行器中心架设置避免了其他部件影响所述天线性能，且保证脚架方便拆卸。
附图说明
图1是本发明实施例示出的一种飞行器的示意图。
图2是本发明实施例示出的一种飞行器的机臂与连接件的连接示意图。
图3是本发明实施例示出的一种飞行器的机臂与连接件的爆炸图。
图4是本发明实施例示出的一种飞行器的机臂组件收起状态示意图。
具体实施方式
这里将详细地对示例性实施例进行说明，其示例表示在附图中。下面的描述涉及附图时，除非另有表示，不同附图中的相同数字表示相同或相似的要素。以下示例性实施例中所描述的实施方式并不代表与本发明相一致的所有实施方 式。相反，它们仅是与如所附权利要求书中所详述的、本发明的一些方面相一致的装置和方法的例子。
在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
实施方式一：
请参阅图1至图4，本实施例示出的一种飞行器100，包括中心架1、天线3及与所述中心架1连接的机臂组件2，其中所述中心架1中设置有电气设备和金属零部件等。在不同的实施例中，所述机臂组件2与所述中心架1可折叠连接或不可折叠连接。
所述机臂组件2包括机臂21，所述天线3设置于所述机臂21上且远离所述中心架1的位置。在所述机臂21上设置所述天线3，使所述天线3远离所述中心架1中的电气设备和金属零部件等，避免电器设备和金属零部件等干扰天线3的信号。在一个实施例中，所述天线3设置在远离所述中心架1、位于所述机臂21的中间或趋于所述机臂21中间的位置。
本发明将飞行器100的天线3设置在所述机臂组件2的机臂21上，在远离所述中心架1的位置，无电气设备和金属零部件的干扰条件下，所述天线3可获得更佳性能。
进一步地，如图2所示，所述飞行器100还包括设置在所述机臂21上的连接件4，所述连接件4用于将所述天线3固定在所述机臂21上。结合上述实施方式可以理解为：所述天线3可直接固定在所述机臂21上，例如将天线3胶接在所述机臂21上；也可以通过一所述连接件4将所述天线3固定在所述机臂21上。
请参阅图2和图3，所述连接件4包括与所述机臂21适配的锁紧套41，及与所述锁紧套41连接的天线座42。所述天线座42用于承载所述天线3。在一实施例中，所述锁紧套41与所述机臂21为可拆卸连接或不可拆卸连接。例如所述锁紧套41与所述机臂21为卡接连接，所述锁紧套41与所述机臂21也可通过螺栓或螺钉固定连接。
请参阅图3，所述天线座42包括本体部421，所述本体部421包括用于 容纳所述天线3的容置空间423。即在所述天线座42内设置所述容置空间423用于承载所述天线3。在一实施例中，所述天线3也可直接放置在所述容置空间423中，并在所述本体部412上设置一挡板424，用于将所述天线3固定在所述容置空间423中。所述挡板424可设置于所述容置空间423的上部。在其他实施例中，所述天线3也可嵌置在所述容置空间423内。
进一步地，所述本体部421还包括位于所述容置空间423上方的过线孔422，该过线孔422可供所述天线3的连接线31穿过。
请参阅图3，所述锁紧套41包括与所述天线座42连接的连接端412，及用于将所述锁紧套41固定在所述机臂21上的锁紧端411。在一实施例中，所述锁紧端411可通过螺钉6将所述锁紧套41固定在所述机臂21上。例如在所锁紧端411上开设有螺钉孔，将螺钉6穿过所述螺钉孔锁紧所述锁紧端411。
所述连接端412内设有塞孔413，所述机臂21上对应所述塞孔413设有布线孔(未示出)。在一实施例中，所述天线3的连接线31穿过所述塞孔413和所述布线孔进入所述机臂21内。将所述天线3的连接线31置于所述机臂21内，可防护所述连接线31不受损坏，避免布线凌乱影响飞行器的外观美。诚然，在其他实施例中，所述连接线31也可直接捆绑在所述机臂21上，或使用固定件将所述连接线31固定在所述机臂21上。
请继续参阅图3，所述塞孔413内可放置用于密封所述塞孔413和所述布线孔的弹性件43。所述弹性件43可选用硅胶塞，所述天线3的连接线31可穿过该硅胶塞。即所述连接线31穿过所述硅胶塞进入所述机臂21中，所述硅胶塞放置在所述塞孔413和所述布线孔内。所述硅胶塞进一步防护了所述连接线31。
进一步地，在一实施例中，所述机臂21打开时，所述天线3位于所述机臂21的下方。所述天线3使用个数选用两根或两根以上，并分别设置在不同的机臂21上。在另一实施例中设置所述天线3的极化方向与水平面垂直，位于所述机臂21的下方。
所述天线3设置在机臂21下方，可保证当所述机臂组件2折叠收起时天线3朝向整个飞行器100的中心，外侧的机臂组件2可对天线3起到保护作用而使天线3免受碰撞等，从而便于包装、搬运、移动。当所述天线3的极化方向与水平面垂直时达到的性能最佳。本实施方式中，所述天线3的延伸方向与所述天线3的极化方向重合，故本实施方式中，设置于所述机臂21上的所述天线3的延伸方向与地面垂直。
可以理解，当所述机臂组件2打开时，所述天线3也可位于所述机臂21的上方，当所述机臂组件3折叠收起时，将所述天线3折叠或转动以便使其朝向所述飞行器100的中心即可，避免留在机臂21外侧受损。
更进一步地，在其他实施例中，所述天线3的极化方向与所述机臂21的延伸方向垂直。机臂21展开时与水平面大致平行，从而设置于机臂21上并与所述机臂21垂直的所述天线3与水平面的夹角也接近九十度。并且在天线3的极化方向与所述机臂21的延伸方向垂直设置，在安装所述天线3时容易校准，也美化了飞行器100的外观。诚然，所述机臂组件2与所述中心架1为不可折叠连接时，所述天线3的极化方向与水平面的夹角也接近九十度，也具有上述效果。本实施方式中，所述天线3的延伸方向与所述天线3的极化方向重合，故本实施方式中，所述天线3的延伸方向与机臂21垂直。
请参阅图4，所述飞行器100还包括起落架组件5，飞行器100的机臂组件2与中心架1可折叠连接。当所述机臂21向下折叠后，整个飞行器100的体积减小。所述天线3则位于所述起落架组件5和所述机臂组件2内侧，所述起落架组件5和所述机臂组件2可对天线3起到保护作用，可防止所述天线3受到损坏。即所述机臂组件2与所述中心架1可折叠连接，当所述机臂组件2处于收起状态时所述天线3朝向所述飞行器100的中心，使所述天线3位于所述起落架组件5和所述机臂组件2内侧以保护天线3不被损坏。
在一实施例中，所述天线为偶极子天线，还可以为例如IFA(Inverted F-shaped Antenna，倒F天线)、PIFA(Planar Inverted F-shaped Antenna，平面倒F天线)、环形天线、缝隙天线等。所述环形天线是将一根金属导 线绕成一定形状，如圆形、方形、三角形等，以导体两端作为输出端的结构。
在一实施例中，所述飞行器100为多旋翼飞行器100，包括四旋翼飞行器、六旋翼飞行器或八旋翼飞行器中的一种。
实施方式二：
请参阅图1至图4。下面通过另一个实施方式对本发明提供一种飞行器100做进一步地说明。所述飞行器100包括中心架1、天线3及与所述中心架1连接的机臂组件2。所述机臂组件2与所述中心架1可折叠连接。所述机臂组件2包括机臂21，所述天线3设置于所述机臂21上，且当所述机臂组件2处于收起状态时所述天线朝向所述飞行器中心，使所述天线3位于所述起落架组件5和所述机臂组件2内侧。
即飞行器100的机臂组件2可相对于所述中心架1张开或收起，将天线3设置在所述机臂21上，所述天线3可随所述机臂21收起，且当所述机臂组件2处于收起状态时所述天线3位于所述起落架组件5和所述机臂组件2内侧。由于所述天线3的外侧有所述起落架组件5和所述机臂组件2，在运输或包装飞行器100时，所述起落架组件5和所述机臂组件2可对天线3起到保护作用而使天线3免受碰撞等，减少外力对天线3的损害。由于将天线3设置在机臂21上，则可以将起落架组件设计成快拆结构，进一步减少飞行器的包装体积，更有利于移动搬运。
在一实施例中，所述机臂21打开时，所述天线3位于所述机臂21的下方，当所述机臂组件2处于收起状态时所述天线3朝向所述飞行器中心或朝向趋于所述飞行器中心。外侧的机臂组件2可对天线3起到保护作用而使天线3免受碰撞等，从而便于包装、搬运、移动。
在另一实施例中，所述机臂21打开时，设置所述天线3的极化方向与水平面垂直，此时天线3的达到的性能最佳。可以理解，当所述机臂组件2打开时，所述天线3也可位于所述机臂21的上方，当所述机臂组件3折叠收起时，将所述天线3折叠或转动以便使其朝向所述飞行器100的中心即可，避免留在机臂21外侧受损。
在其他实施例中，例如所述天线3的极化方向与所述机臂21的延伸方向垂直。当所述天线3的极化方向与水平面垂直时，所述天线3达到的性能最佳。故本实施方式中的天线3的设置方式在防护所述天线3的同时使所述天线3性能最佳。机臂21展开时与水平面大致平行，从而设置于机臂21上并与所述机臂21垂直的所述天线3与水平面的夹角也接近九十度。并且在天线3的极化方向与所述机臂21的延伸方向垂直设置，在安装所述天线3时容易校准，也美化了飞行器100的外观。
在本实施例中的飞行器100还包括以下技术特征，以下所述技术特征与上一实施例中的技术特征相同或相似，所取得的技术效果也相同或相似，属于同一发明构思。以下仅叙述所述飞行器100的技术特征及技术特征之间关系，不再赘述其具体效果或技术特征之间的作用，具体可参考以上对所述飞行器100实施例的描述。
所述飞行器100还包括：
设置在所述机臂21上的连接件4，所述连接件4用于将所述天线3固定在所述机臂21上。
所述连接件4包括与所述机臂21适配的锁紧套41，及与所述锁紧套41连接的天线座42，所述天线座42用于承载所述天线3。
所述天线座42包括本体部421，所述本体部421包括用于容纳所述天线3的容置空间423。
所述本体部421还包括位于所述容置空间423上方的过线孔422。
所述锁紧套41包括与所述天线座42连接的连接端412，及用于将所述锁紧套41固定在所述机臂21上的锁紧端411。
所述连接端412内设有塞孔413，所述机臂21上对应所述塞孔413设有布线孔，所述天线3的连接线31穿过所述塞孔413和所述布线孔进入所述机臂21内。
所述塞孔413内可放置用于密封所述塞孔413和所述布线孔的弹性件43。
所述天线为偶极子天线。
所述飞行器100为多旋翼飞行器100，包括四旋翼飞行器、六旋翼飞行器或八旋翼飞行器中的一种。
由以上实施方式可知，所述飞行器100将天线3设置在机臂21上，解决了干扰问题，可获得比天线3设置在中心架1上更性能效果。将天线设置在机臂下方，在应用于可折叠机臂组件的飞行器上时，可避免天线损坏。有些带有收放起落架组件5的飞行器，采用天线3设计在机臂21上的方案，就可以将收放起落架组件设计成快拆结构，可进一步减少飞行器的包装体积，更有利于移动搬运。
以上所述仅为本发明的较佳实施例而已，并不用以限制本发明，凡在本发明的精神和原则之内，所做的任何修改、等同替换、改进等，均应包含在本发明保护的范围之内。
本专利文件披露的内容包含受版权保护的材料。该版权为版权所有人所有。版权所有人不反对任何人复制专利与商标局的官方记录和档案中所存在的该专利文件或者该专利披露。

Claims (21)

  1. 一种飞行器，其特征在于，包括中心架、天线，及与所述中心架连接的机臂组件；
    所述机臂组件包括机臂，所述天线设置于所述机臂上且远离所述中心架的位置。
  2. 根据权利要求1所述的飞行器，其特征在于，还包括设置在所述机臂上的连接件，所述连接件用于将所述天线固定在所述机臂上。
  3. 根据权利要求2所述的飞行器，其特征在于，所述连接件包括与所述机臂适配的锁紧套，及与所述锁紧套连接的天线座，所述天线座用于承载所述天线。
  4. 根据权利要求3所述的飞行器，其特征在于，所述天线座包括本体部，所述本体部包括用于容纳所述天线的容置空间。
  5. 根据权利要求4所述的飞行器，其特征在于，所述本体部还包括位于所述容置空间上方的过线孔。
  6. 根据权利要求3所述的飞行器，其特征在于，所述锁紧套包括与所述天线座连接的连接端，及用于将所述锁紧套固定在所述机臂上的锁紧端。
  7. 根据权利要求6所述的飞行器，其特征在于，所述连接端内设有塞孔，所述机臂上对应所述塞孔设有布线孔，所述天线的连接线穿过所述塞孔和所述布线孔进入所述机臂内。
  8. 根据权利要求7所述的飞行器，其特征在于，所述塞孔内可放置用于密封所述塞孔和所述布线孔的弹性件。
  9. 根据权利要求1所述的飞行器，其特征在于，所述机臂打开时，所述天线位于所述机臂的下方；或者
    所述机臂打开时，所述天线的极化方向与水平面垂直；或者
    所述天线的极化方向与所述机臂的延伸方向垂直。
  10. 根据权利要求1所述的飞行器，其特征在于，所述天线为偶极子天 线。
  11. 根据权利要求1至10任一项所述的飞行器，其特征在于，所述飞行器还包括起落架组件，所述机臂组件与所述中心架可折叠连接；当所述机臂组件处于收起状态时所述天线朝向所述飞行器中心，使所述天线位于所述起落架组件和所述机臂组件内侧。
  12. 一种飞行器，其特征在于，包括中心架、天线及与所述中心架连接的机臂组件；所述机臂组件与所述中心架可折叠连接；
    所述机臂组件包括机臂，所述天线设置于所述机臂上，且当所述机臂组件处于收起状态时所述天线朝向所述飞行器中心，使所述天线位于所述起落架组件和所述机臂组件内侧。
  13. 根据权利要求12所述的飞行器，其特征在于，还包括设置在所述机臂上的连接件，所述连接件用于将所述天线固定在所述机臂上。
  14. 根据权利要求13所述的飞行器，其特征在于，所述连接件包括与所述机臂适配的锁紧套，及与所述锁紧套连接的天线座，所述天线座用于承载所述天线。
  15. 根据权利要求14所述的飞行器，其特征在于，所述天线座包括本体部，所述本体部包括用于容纳所述天线的容置空间。
  16. 根据权利要求15所述的飞行器，其特征在于，所述本体部还包括位于所述容置空间上方的过线孔。
  17. 根据权利要求14所述的飞行器，其特征在于，所述锁紧套包括与所述天线座连接的连接端，及用于将所述锁紧套固定在所述机臂上的锁紧端。
  18. 根据权利要求17所述的飞行器，其特征在于，所述连接端内设有塞孔，所述机臂上对应所述塞孔设有布线孔，所述天线的连接线穿过所述塞孔和所述布线孔进入所述机臂内。
  19. 根据权利要求18所述的飞行器，其特征在于，所述塞孔内可放置用于密封所述塞孔和所述布线孔的弹性件。
  20. 根据权利要求12所述的飞行器，其特征在于，所述天线位于所述机 臂的下方；或者
    所述机臂打开时，所述天线的极化方向与水平面垂直；或者
    所述天线的极化方向与所述机臂的延伸方向垂直。
  21. 根据权利要求12所述的飞行器，其特征在于，所述天线为偶极子天线。
PCT/CN2016/111920 2016-11-18 2016-12-24 飞行器 Ceased WO2018090435A1 (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201680088323.8A CN109562821A (zh) 2016-11-18 2016-12-24 飞行器

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201621247756.7U CN206218204U (zh) 2016-11-18 2016-11-18 飞行器
CN201621247756.7 2016-11-18

Publications (1)

Publication Number Publication Date
WO2018090435A1 true WO2018090435A1 (zh) 2018-05-24

Family

ID=58791648

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/111920 Ceased WO2018090435A1 (zh) 2016-11-18 2016-12-24 飞行器

Country Status (2)

Country Link
CN (2) CN206218204U (zh)
WO (1) WO2018090435A1 (zh)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206893798U (zh) 2017-07-10 2018-01-16 深圳市道通智能航空技术有限公司 一种天线及无人机
CN107512391B (zh) * 2017-08-23 2020-07-24 佛山长光智能制造研究院有限公司 基于系留线缆供电的旋翼无人飞行器
CN109415127B (zh) * 2017-12-01 2022-03-04 深圳市大疆灵眸科技有限公司 连接组件以及拍摄设备
CN109774948A (zh) * 2019-02-13 2019-05-21 山东蜂巢航空科技有限公司 一种可挂载多种载荷的油电混合多旋翼无人机
WO2024124569A1 (zh) * 2022-12-16 2024-06-20 深圳市闪至科技有限公司 一种无人飞行器

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2455374A (en) * 2008-06-16 2009-06-10 Middlesex University Higher Ed Unmanned aerial vehicle comprising a triangular array of rotors
CN204660021U (zh) * 2015-03-12 2015-09-23 上海良相智能化工程有限公司 一种六旋翼无人侦察直升机系统
CN204776013U (zh) * 2015-06-04 2015-11-18 东莞中寰智能航空科技有限公司 一种六轴无人机
CN205186516U (zh) * 2015-10-26 2016-04-27 贵州斯凯威科技有限公司 一种具有运输功能的无人机
CN105752340A (zh) * 2016-04-07 2016-07-13 广州极飞电子科技有限公司 无人飞行器

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9731811B2 (en) * 2013-12-13 2017-08-15 Aai Corporation Payload shroud for air vehicle
WO2015196418A1 (zh) * 2014-06-26 2015-12-30 深圳市大疆创新科技有限公司 一种飞行器及其信号线保护组件
CN205652331U (zh) * 2016-04-14 2016-10-19 深圳市大疆创新科技有限公司 无人飞行器的机架及多旋翼无人飞行器

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2455374A (en) * 2008-06-16 2009-06-10 Middlesex University Higher Ed Unmanned aerial vehicle comprising a triangular array of rotors
CN204660021U (zh) * 2015-03-12 2015-09-23 上海良相智能化工程有限公司 一种六旋翼无人侦察直升机系统
CN204776013U (zh) * 2015-06-04 2015-11-18 东莞中寰智能航空科技有限公司 一种六轴无人机
CN205186516U (zh) * 2015-10-26 2016-04-27 贵州斯凯威科技有限公司 一种具有运输功能的无人机
CN105752340A (zh) * 2016-04-07 2016-07-13 广州极飞电子科技有限公司 无人飞行器

Also Published As

Publication number Publication date
CN109562821A (zh) 2019-04-02
CN206218204U (zh) 2017-06-06

Similar Documents

Publication Publication Date Title
WO2018090435A1 (zh) 飞行器
CN108698685B (zh) 无人飞行器及其机架、套件、组装方法、以及操作方法
EP3227957B1 (en) Multi-panel antenna system
US9853353B2 (en) Space vehicle electromechanical system and helical antenna winding fixture
CN204289684U (zh) 天线组件、起落架及无人飞行器
CN105000163A (zh) 一种向下折叠式多旋翼无人飞行器
US20050057420A1 (en) Low profile sector antenna configuration
US10396443B2 (en) Integrated antenna in an aerial vehicle
US10283877B2 (en) Multipolarized vector sensor array antenna system for radio astronomy applications
US3665478A (en) Foldable antenna operable in dual modes
WO2011091749A1 (zh) 数据卡
US10084499B2 (en) Mobile computing device holder
JPWO2019030832A1 (ja) 無人飛行体、及び受電コイルユニット
US10707564B2 (en) Unmanned aerial vehicle
US20150318612A1 (en) Method and Apparatus for Wideband, Polarimetric Reception of High Frequency Radio Signals
CN105789846B (zh) 圆极化天线及电子设备
WO2019029387A1 (zh) 飞行器及其机臂组件和机架
WO2016177193A1 (zh) 一种伸缩走线槽及硬盘阵列插箱
US20160276736A1 (en) External Antenna
WO2020019147A1 (zh) 无人飞行器及其天线
CN204833666U (zh) 一种遥控器及具有其的无人机组件
WO2019095770A1 (zh) 一种天线装置及具有该天线装置的遥控器、无人机组件
US12046918B2 (en) Recovery units for non-proximity wireless power transfer
US11378606B2 (en) Switchboard controller for manual adaptation of radiation patterns and measurements of steerable parasitic array antenna
CN205609727U (zh) Lte全向车载天线

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: 16921979

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: 16921979

Country of ref document: EP

Kind code of ref document: A1