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WO2016141742A1 - 一种可快速拆卸安装固定翼无人飞行器 - Google Patents

一种可快速拆卸安装固定翼无人飞行器 Download PDF

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Publication number
WO2016141742A1
WO2016141742A1 PCT/CN2015/097380 CN2015097380W WO2016141742A1 WO 2016141742 A1 WO2016141742 A1 WO 2016141742A1 CN 2015097380 W CN2015097380 W CN 2015097380W WO 2016141742 A1 WO2016141742 A1 WO 2016141742A1
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Prior art keywords
wing
fixed
tail
fuselage
quick
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PCT/CN2015/097380
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English (en)
French (fr)
Inventor
杨华东
吴奇才
赵江
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    • 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
    • B64C3/00—Wings

Definitions

  • This application belongs to the field of aerial photography, and in particular relates to a UAV that can be quickly disassembled and installed.
  • Unmanned aerial vehicles are characterized by small size, light weight, low cost, flexible operation and high safety. They can be widely used in aerial photography, monitoring, search and rescue, resource exploration and other fields.
  • the existing fixed-wing unmanned aerial vehicles because the left and right wings and the tail fins are long, occupy a large space and are not convenient to carry and transport.
  • the antenna of the fixed-wing UAV is usually installed on the top of the fuselage main body. Since the antenna is located above, there is a problem of poor signal on the one hand, and on the other hand, because the antenna protrudes from the top, it is easy to occur during transportation or movement. Collision and damage.
  • the present invention provides the following technical solutions:
  • the embodiment of the present application discloses a quick release and installation of a fixed wing unmanned aerial vehicle, including a fuselage main body and a wing and a tail mounted on the fuselage main body, the tail portion including a tail wing and being fixed to the fuselage main body and the tail wing
  • the tail shaft is provided with a tail rod passage, and one end of the tail rod is installed in the tail rod passage, and the depth of the tail rod inserted in the tail rod passage is adjustable.
  • the tailstock passage extends through the fuselage body.
  • the body of the fuselage comprises a skeleton and a casing mounted on an outer side of the skeleton, the skeleton comprising a horizontally disposed supporting plate, and two of the supporting plates Side symmetrically mounted with a reinforcing plate, the reinforcing plate being disposed perpendicular to the supporting plate, A fixing bracket is mounted above the support plate, and the tail rod passage is formed between the fixing bracket and the support plate.
  • the fixing bracket is provided with a fixing hole
  • the supporting plate is provided with a screw hole
  • the tail rod is provided with a through hole
  • the fixing hole, the screw hole and the through hole correspond to each other.
  • the support plate is provided with a plurality of lightening holes.
  • the front end of the support plate is fixed with an on-hook plate
  • the hung plate is provided with a vertical support plate
  • the hanging plate is provided with a suspension for hanging an aerial camera.
  • the outer side of the hanging board is covered with a hood, and the hood is detachably mounted between the hood and the body.
  • the upper surface of the fuselage main body is recessed to form a umbrella compartment space, and the upper of the umbrella compartment space is covered with an umbrella compartment cover, the umbrella compartment cover It is detachable and fixed from the body of the fuselage.
  • the bottom of the fuselage main body is recessed upwardly to form an on-hook space, and the opening of the hanging space covers the bottom cover, and the bottom cover is
  • the body of the fuselage is detachable and fixed.
  • the wing comprises a middle wing, a left wing and a right wing, and the middle wing is fixed on the fuselage body,
  • the left wing and the right wing are respectively detachably mounted on the left and right sides of the middle wing.
  • the ends of the left and right wing respectively extend with a guide rod
  • the end of the middle wing is provided to accommodate the a mounting hole of the guide rod
  • the guiding rod includes a first guiding rod and a second guiding rod which are juxtaposed, the first guiding rod has a larger diameter and an extended length than the second guiding rod, and the second guiding rod
  • the diameter is gradually reduced in a direction away from the left or right wing
  • a limiting phase is fixed between the left wing and the middle wing, and between the right wing and the middle wing respectively a latch that moves relative to the adjacent wing
  • the buckle includes two elastic arms formed by bending from the middle portion, and the two elastic arms are concavely formed at opposite positions to form a latching portion, and the latching portion has an arc a shape-shaped surface, the ends of the two elastic arms are respectively bent outward to form an extension arm, and the two extension arms have a figure
  • the two sides of the wing are respectively mounted with a rotor in a symmetrical position, and each of the rotors is respectively driven by a motor, and the rear of the motor is formed.
  • There is a heat dissipation channel the heat dissipation channel is located below the wing, and an antenna is installed in one of the heat dissipation channels; the antenna is rotatable between a horizontal direction and a vertical direction.
  • the present invention performs three-stage splitting on the entire wing with a large size, wherein the middle wing can integrate electronic circuit equipment such as flying air and receiving, and there is no need to disassemble from the main body of the fuselage.
  • the left and right wings can be removed to save space and facilitate transportation.
  • the tail rod can reduce the occupied space by inserting the front
  • the antenna is installed under the wing and shares the heat dissipation channel with the motor. It does not occupy the upper and lower space, and the contact collision is not easy to occur during the movement, and the antenna is located below, and the communication signal is good.
  • FIG. 1 is a perspective view of a fixed-wing UAV in accordance with an embodiment of the present invention
  • FIG. 2 is a schematic exploded view of a fixed-wing UAV in accordance with an embodiment of the present invention
  • FIG. 3 is a schematic structural view showing a skeleton of a fixed-wing UAV in a specific embodiment of the present invention
  • FIG. 4 is a schematic view showing the fixing between the buckle and the mounting plate in the specific embodiment of the present invention.
  • Figure 5 is a cross-sectional view taken along line A-A of Figure 4.
  • Figure 6 is a bottom plan view of a fixed-wing UAV in accordance with an embodiment of the present invention.
  • FIG. 7 is a perspective view showing the front end of the tail rod after the front end of the embodiment of the present invention.
  • the fixed wing unmanned aerial vehicle includes a fuselage main body 10, and a wing 20 and a tail portion 30 mounted on the fuselage main body 10, and the tail portion 30 includes a tail fin 31 and is fixed to the fuselage main body 10 and the rear wing. 31 between the tail bar 32.
  • the wing 20 includes a middle wing 21, a left wing 22 and a right wing 23, wherein the middle wing 21 is fixed to the fuselage main body 10, and the left wing 22 and the right wing 23 are detachably mounted respectively. On the left and right sides of the middle wing 21.
  • the three-stage splitting is performed on the entire wing with a large size, wherein the middle wing can integrate electronic circuit equipment such as flying air and receiving, and there is no need to disassemble between the main body and the fuselage body.
  • the left and right wings can be removed to save space and facilitate transportation.
  • the ends of the left wing 22 and the right wing 23 respectively extend a guiding rod 221, and the end fitting guide 221 of the middle wing 21 is provided with a mounting hole 211, and the left wing 22 and the right wing 23 can be
  • the middle wing 21 is fast fixed by the guide rod 221.
  • the guide bars 221 are provided in parallel. When only one guide bar 221 is provided, it is preferably flat.
  • the left wing 22 or the right wing 23 are respectively inserted into the mounting holes of the middle wing through two guiding rods, so that quick assembly and disassembly can be realized, and two guiding rods can be avoided. After assembly, the left or right wing and the middle wing are rotated relative to each other.
  • a buckle 40 is fixed between the left wing 22 and the middle wing 21, and between the right wing 23 and the middle wing 21, respectively, and the middle wing 21 and the left respectively After the segment wing 22 and the right wing 23 are assembled, the buckle 40 is used to achieve relative fixation of the butt joint, thereby preventing the left wing 22 and the right wing 23 from being dialed from the middle wing 21 after being fixed. Out.
  • the buckle 40 includes two elastic arms 41 formed by bending from the middle portion.
  • the two elastic arms 41 are recessed at opposite positions to form a holding portion 42 having a curved surface.
  • the ends of the two elastic arms 41 are respectively bent outward to form an extension arm 43, and the two extension arms 43 have a figure-eight opening therebetween.
  • the first mounting plate is fixed on the end faces of the two sides of the middle wing 21 respectively. 212.
  • the second mounting plate 222 is fixed to the end surface of the left wing 22 and the right wing 23.
  • the first mounting plate 212 and the second mounting plate 222 are respectively provided with corresponding holes 222.
  • An insertion port 231 for inserting the elastic arm 41 of the buckle 40 is respectively disposed on the middle wing 21, the left wing 22 and the right wing 23.
  • the insertion port 231 is disposed adjacent to the first mounting plate 212 or the second mounting plate 222.
  • the first mounting plate 212 and the second mounting plate 222 are fitted together, and the card holes on the two mounting plates are opposite.
  • the ends of the first mounting plate 212 and the second mounting plate 222 are squeezed between the two elastic arms 41 through the figure-eight opening between the two extending arms 43, and the two elastic arms 41 of the buckle 40 are respectively inserted into the middle wing 21
  • the insertion opening 231 of the left wing 22 further pushes the buckle 40 until the two holding portions 42 slide into the holes of the two mounting plates, respectively.
  • the buckle 40 does not fall off from the insertion opening 231 after the engagement is completed, and the left wing 22 and the right wing 23 can be restrained from the middle wing 21 by the buckle 40, when the left wing is required When the 22nd and the right wing 23 are detached, the buckle 40 can be directly pulled out.
  • the card hole 2221 can also be provided as a groove, and a plurality of buckles can also be arranged between the first mounting plate 212 and the second mounting plate 222.
  • the body main body 10 is provided with a tail rod passage, one end of the tail rod 32 is installed in the tail rod passage, and the length of the tail rod 32 contracted in the tail rod passage is adjustable. Further, the tail boom passage extends through the fuselage body 10, that is, the tail boom 32 can be inserted beyond the head of the fuselage body 10. The structure after the tail bar 32 is contracted is as shown in FIG.
  • the tail rod 32 can be inserted forward to shorten the space occupied by the entire tail portion 30, which is convenient to disassemble, saves space, is convenient to transport, and is convenient to carry.
  • the tail boom 32 can be pulled out to the corresponding position and the tail boom 32 can be relatively fixed to the fuselage body 10.
  • the fuselage main body 10 includes a skeleton and a casing mounted on the outer side of the skeleton.
  • the skeleton includes a horizontally disposed support plate 11.
  • Symmetrical plates 12, reinforcing plates 12 and support plates are symmetrically mounted on both sides of the support plate 11.
  • a plurality of lightening holes 111 are defined in the support plate 11.
  • the skeleton structure is simple, the weight of the body is greatly reduced, and the support plate 11 is fixed to the casing through the reinforcing plate 12, so that the contact surface between the skeleton and the casing can be increased, so that the skeleton and the casing are more stable. Moreover, the support plate 11 is also not easily bent and deformed.
  • a fixing bracket 13 is mounted above the support plate 11, and the tail rod passage is formed on the fixing bracket 13 and the branch Between the risers 11 .
  • the fixing bracket 13 is provided with a fixing hole.
  • the supporting plate 11 is provided with a screw hole below the fixing hole, and the tail rod is provided with a through hole.
  • the middle wing 21 includes two support rods 213 arranged side by side, and the two support rods 213 are fixed to the body main body 10 by screws. When disassembling and transporting, the middle wing 21 need not be detached from the fuselage main body 10, and the middle wing 21 and the fuselage main body 10 can be transported as a whole.
  • a hanging plate 14 is fixed to the front end of the supporting plate 11, and the hanging plate 14 is vertically disposed.
  • the hanging plate 14 is provided with a hanging hole for hanging the aerial camera.
  • the outer side of the hanging board 14 is covered with a head cover 50, and the head cover 50 is detachably mounted with the body main body 10.
  • the head cover 50 is first removed, and then the aerial camera is hung on the hanging board 14, the aerial photography is finished, the aerial camera is removed, and the head cover 50 is covered.
  • the left wing 22 and the right wing 23 are respectively mounted with a rotor 61 at a symmetrical position, and each of the rotors 61 is driven by a motor 62, wherein a heat dissipation passage 63 is formed behind the motor 62 on the left wing 22.
  • An antenna 70 is mounted in the heat dissipation passage 63, and the antenna 70 is rotatable between a horizontal direction and a vertical direction.
  • the antenna 70 is mounted below the left wing 22.
  • the antenna 70 can also be mounted in the heat dissipation channel of the right wing 23.
  • the antenna 70 is installed under the wing, and the communication effect is good on the one hand, and the space at the top of the body main body 10 is not occupied on the other hand, and the umbrella space is provided above the main body of the fuselage. Moreover, the antenna 70 skillfully utilizes the heat dissipation space of the motor 62, which not only facilitates heat dissipation, but also does not require additional space. When transporting, the antenna can be rotated to a horizontal position without taking up space.
  • a cabin space 15 is formed in the upper portion of the fuselage main body 10, and an umbrella cover 16 is covered above the umbrella compartment space 15, and the umbrella cover 16 is detachably fixed to the fuselage main body 10.
  • the bottom of the fuselage main body 10 is recessed upwardly to form an on-hook space 17, and the opening of the hanging space 17 covers the bottomed cover 18, and the bottom cover 18 is detachably fixed to the body 10.
  • the aerial camera head can be hung in the hanging space 17 as needed, which is convenient for shooting and framing.
  • a camera mounting camera is respectively disposed at the head and the bottom of the body main body 10. Location, so there are many different options available to users.

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Abstract

本申请公开了一种可快速拆卸安装固定翼无人飞行器，包括机身主体、以及安装于机身主体上的机翼和尾部，所述尾部包括尾翼以及固定在机身主体和尾翼之间的尾杆，所述机身主体上设有一尾杆通道，所述尾杆的一端安装于所述尾杆通道内，所述尾杆插置于所述尾杆通道内的深度可调。本发明的可快速拆卸安装固定翼无人飞行器，在运输过程中，尾杆可以通过前插减少占用空间。

Description

一种可快速拆卸安装固定翼无人飞行器 技术领域
本申请属于航拍技术领域，特别是涉及一种可快速拆卸安装固定翼无人飞行器。
背景技术
无人飞行器具有体积小、重量轻、费用低、操作灵活和安全性高的特点，可广泛应用于航拍、监测、搜救、资源勘查等领域。
现有的固定翼无人飞行器，由于左右机翼以及尾翼较长，占用空间大，不便于携带和运输。另外，固定翼无人飞行器的天线通常安装于机身主体的顶部，由于天线位于上方，一方面存在信号不良的问题，另一方面，由于天线凸伸于顶部，在运输或移动过程中容易发生碰撞而造成损坏。
有鉴于此，有必要提供一种新型的固定翼无人飞行器。
发明内容
本发明的目的在于提供一种可快速拆卸安装固定翼无人飞行器，以克服现有技术中的不足。
为实现上述目的，本发明提供如下技术方案：
本申请实施例公开了一种可快速拆卸安装固定翼无人飞行器，包括机身主体、以及安装于机身主体上的机翼和尾部，所述尾部包括尾翼以及固定在机身主体和尾翼之间的尾杆，所述机身主体上设有一尾杆通道，所述尾杆的一端安装于所述尾杆通道内，所述尾杆插置于所述尾杆通道内的深度可调。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述尾杆通道贯穿所述机身主体。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述机身主体包括骨架以及安装于骨架外侧的壳体，所述骨架包括一水平设置的支撑板，所述支撑板的两侧对称安装有加强板，所述加强板与支撑板垂直设置，所述 支撑板的上方安装有固定支架，所述尾杆通道形成于所述固定支架与支撑板之间。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述固定支架上开设有固定孔，所述支撑板上设有螺孔，所述尾杆上开设有通孔，所述的固定孔、螺孔和通孔上下对应。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述支撑板上开设有多个减重孔。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述支撑板的前端固定有一挂机板，所述挂机板垂直支撑板设置，所述挂机板上开设有用以悬挂航拍相机的悬挂孔，所述挂机板的外侧遮盖有头罩，所述头罩与机身主体之间可拆卸安装。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述机身主体的上方凹设形成有一伞仓空间，所述伞仓空间的上方遮盖有伞仓盖，所述伞仓盖与机身主体之间可拆卸固定。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述机身主体的下方向上凹设形成有一挂机空间，该挂机空间的开口处遮盖有底仓盖，所述底仓盖与机身主体之间可拆卸固定。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述机翼包括中段机翼、左段机翼和右段机翼，所述中段机翼固定于所述机身主体上，所述左段机翼和右段机翼分别可拆卸安装于中段机翼的左右两侧。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述左段机翼和右段机翼的端部分别延伸有导杆，所述中段机翼的端部设有容纳所述导杆的安装孔，所述导杆包括并列设置的第一导杆和第二导杆，所述第一导杆的直径和延伸长度均大于所述第二导杆，所述第二导杆的直径沿背离所述左段机翼或右段机翼的方向逐渐减小，所述左段机翼与中段机翼之间、以及右段机翼与中段机翼之间分别固定有限制相邻机翼间相对移动的卡扣，所述卡扣包括从中部折弯形成的两个弹性臂，该两个弹性臂于相对位置相向凹设形成有卡持部，所述卡持部具有弧形表面，所述两个弹性臂的末端分别向外折弯形成有延伸臂，所述两个延伸臂之间呈八字形开口，所述中段机翼两侧的端 面上分别固定有第一安装板，所述左段机翼和右段机翼的端面上固定有第二安装板，所述第一安装板和第二安装板上于对应位置上分别设有卡孔或卡槽，所述中段机翼、左段机翼和右段机翼上分别设有供所述卡扣弹性臂插入的插入口，所述插入口贴近所述第一安装板或第二安装板设置。
优选的，在上述的可快速拆卸安装固定翼无人飞行器中，所述机翼的两侧在对称位置上分别安装有一旋翼，所述每个旋翼分别通过一电机驱动，所述电机的后方形成有一散热通道，所述散热通道位于所述机翼的下方，其中一所述散热通道内安装有天线；所述天线在水平方向和垂直方向之间可转动。
与现有技术相比，本发明的优点在于：
(1)、本发明对于尺寸较大的整个机翼进行三段式拆分，其中中段机翼可整合飞空、接收等电子电路设备，其与机身主体之间无需拆卸。在运输过程中，可以将左段机翼和右段机翼拆卸下来，节约空间，方便运输。
(2)、三段机翼完成拼装后，通过卡扣可以限制机翼之间的分离。
(3)、运输过程中，尾杆可以通过前插减少占用空间；
(4)、天线安装于机翼的下方，与电机共用散热通道，不占用上下空间，而且移动过程中不易发生接触碰撞，而且天线位于下方，通信信号好。
附图说明
为了更清楚地说明本申请实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本申请中记载的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1所示为本发明具体实施例中固定翼无人飞行器的立体示意图；
图2所示为本发明具体实施例中固定翼无人飞行器的爆炸示意图；
图3所示为本发明具体实施例中固定翼无人飞行器骨架的结构示意图；
图4所示为本发明具体实施例中卡扣与安装板之间的固定示意图；
图5所示为图4中A-A的剖视图；
图6所示为本发明具体实施例中固定翼无人飞行器的仰视图；
图7所示为本发明具体实施例中尾杆前插后的立体示意图。
具体实施方式
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详细的描述，显然，所描述的实施例仅仅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，本领域普通技术人员在没有做出创造性劳动的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。
参图1和图2所示，固定翼无人飞行器包括机身主体10、以及安装于机身主体10上的机翼20和尾部30，尾部30包括尾翼31以及固定在机身主体10和尾翼31之间的尾杆32。
机翼20包括中段机翼21、左段机翼22和右段机翼23，其中，中段机翼21固定在机身主体10上，左段机翼22和右段机翼23分别可拆卸安装于中段机翼21的左右两侧。
在该技术方案中，对于尺寸较大的整个机翼进行三段式拆分，其中中段机翼可整合飞空、接收等电子电路设备，其与机身主体之间无需拆卸。在运输过程中，可以将左段机翼和右段机翼拆卸下来，节约空间，方便运输。
左段机翼22和右段机翼23的端部分别延伸有导杆221，中段机翼21的端部配合导杆221设有安装孔211，左段机翼22和右段机翼23可以通过导杆221实现与中段机翼21快速固定。导杆221优选并列设置有2个。导杆221仅设置有1个时，其优选为扁平状。
在该技术方案中，左段机翼22或右段机翼23分别通过两根导杆插接在中段机翼的安装孔中，可以实现快速的组装和拆卸，采用两根导杆，可以避免组装后左段机翼或右段机翼与中段机翼间发生相对转动。
参图4和图5所示，左段机翼22与中段机翼21之间、以及右段机翼23与中段机翼21之间分别固定有卡扣40，当中段机翼21分别与左段机翼22以及右段机翼23完成组装后，卡扣40用以实现对接处的相对固定，因此可以防止左段机翼22和右段机翼23在固定后从中段机翼21上拨出。
卡扣40包括从中部折弯形成的两个弹性臂41，该两个弹性臂41于相对位置相向凹设形成有卡持部42，卡持部42具有弧形表面。两个弹性臂41的末端分别向外折弯形成有延伸臂43，两个延伸臂43之间呈八字形开口。
结合图3和图6所示，中段机翼21两侧的端面上分别固定有第一安装板 212，左段机翼22和右段机翼23的端面上固定有第二安装板222，第一安装板212和第二安装板222上于对应位置上分别设有卡孔2221。
中段机翼21、左段机翼22和右段机翼23上分别设有供卡扣40弹性臂41插入的插入口231，插入口231贴近第一安装板212或第二安装板222设置。
当中段机翼21分别与左段机翼22以及右段机翼23完成组装后，第一安装板212与第二安装板222贴合，同时两个安装板上的卡孔相对。第一安装板212和第二安装板222的末端通过两个延伸臂43之间的八字形开口挤入两个弹性臂41之间，卡扣40的两个弹性臂41分别插入中段机翼21和左段机翼22上的插入口231内，进一步推动卡扣40直至两个卡持部42分别滑入两个安装板上的卡孔内。如此，卡扣40完成卡合后不会从插入口231脱落，同时通过卡扣40可以限制左段机翼22和右段机翼23从中段机翼21上脱落，当需要将左段机翼22和右段机翼23拆卸时，直接将卡扣40拔出即可。
易于想到的是，卡孔2221还可以设置成凹槽，第一安装板212和第二安装板222之间也可以设置多个卡扣。
机身主体10上设有一尾杆通道，尾杆32的一端安装于该尾杆通道内，且尾杆32收缩在尾杆通道内的长度可调。进一步地，尾杆通道贯穿机身主体10，即尾杆32可通过穿插超出机身主体10的头部。尾杆32收缩后的结构如图7所示。
在该技术方案中，可以将尾杆32向前穿插以缩短整个尾部30所占用的空间，拆卸方便、节约空间、方便运输、便于携带。当使用时，可以将尾杆32拔出到相应位置，然后将尾杆32与机身主体10相对固定。
参图3所示，机身主体10包括骨架以及安装于骨架外侧的壳体，骨架包括一水平设置的支撑板11，支撑板11的两侧对称安装有加强板12，加强板12与支撑板11垂直设置。支撑板11上开设有多个减重孔111。
在该技术方案中，骨架结构简单，大大降低了机体的重量，支撑板11通过加强板12与壳体固定，可以增加骨架与壳体之间的接触面，使得骨架与壳体之间更加稳固，而且，支撑板11也不易弯折变形。
支撑板11的上方安装有固定支架13，尾杆通道形成于固定支架13与支 撑板11之间。固定支架13上开设有固定孔，支撑板11上对应该固定孔的下方设有螺孔，尾杆上开设有通孔，在组装时，首先将尾杆上通孔与固定支架上的固定孔对应，然后将螺丝分别穿过固定孔和通孔并与支撑板上的螺孔固定，从而实现尾杆与机身主体之间的相对固定。当需要拆卸运输时，松开螺丝并将螺丝拔出，尾杆前插即可。
中段机翼21包括两根并列设置的支撑杆213，该两根支撑杆213通过螺钉固定在机身主体10上。在拆卸运输时，中段机翼21无需从机身主体10上拆卸，中段机翼21和机身主体10可以作为一个整体进行运输。
支撑板11的前端固定有一挂机板14，挂机板14垂直支撑板11设置，挂机板14上开设有用以悬挂航拍相机的悬挂孔。挂机板14的外侧遮盖有头罩50，头罩50与机身主体10之间可拆卸安装。
在需要航拍作业时，先将头罩50拆下，然后将航拍相机悬挂在挂机板14上，航拍结束，取下航拍相机并将头罩50盖上。
左段机翼22和右段机翼23在对称位置上分别安装有一旋翼61，每个旋翼61分别通过一电机62驱动，其中，左段机翼22上的电机62的后方形成有一散热通道63，该散热通道63内安装有天线70，天线70可以在水平方向和垂直方向之间转动。天线70安装于左段机翼22的下方。
易于想到的是，天线70还可以安装在右段机翼23的散热通道内。
天线70安装于机翼的下方，一方面通信效果好，另一方面不占用机身主体10顶端的空间，为机身主体上方设置伞仓空间提供可能。而且，天线70巧妙利用了电机62的散热空间，不仅散热方便，而且不额外占用空间。在运输时，天线可以转动至水平位置，不占用空间。
机身主体10的上方凹设形成有一伞仓空间15，伞仓空间15的上方遮盖有伞仓盖16，伞仓盖16与机身主体10之间可拆卸固定。
在该技术方案中，通过预留伞仓空间15，方便用户根据需要安装降落伞。
机身主体10的下方向上凹设形成有一挂机空间17，挂机空间17的开口处遮盖有底仓盖18，底仓盖18与机身主体10之间可拆卸固定。
该该技术方案中，可以根据需要在挂机空间17内悬挂航拍相机云台，便于拍摄取景。本案中在机身主体10的头部和底部分别设置了一个安装相机的 位置，因此为用户提供了多种不同的选择。
需要说明的是，在本文中，诸如第一和第二等之类的关系术语仅仅用来将一个实体或者操作与另一个实体或操作区分开来，而不一定要求或者暗示这些实体或操作之间存在任何这种实际的关系或者顺序。而且，术语“包括”、“包含”或者其任何其他变体意在涵盖非排他性的包含，从而使得包括一系列要素的过程、方法、物品或者设备不仅包括那些要素，而且还包括没有明确列出的其他要素，或者是还包括为这种过程、方法、物品或者设备所固有的要素。在没有更多限制的情况下，由语句“包括一个……”限定的要素，并不排除在包括所述要素的过程、方法、物品或者设备中还存在另外的相同要素。
以上所述仅是本申请的具体实施方式，应当指出，对于本技术领域的普通技术人员来说，在不脱离本申请原理的前提下，还可以做出若干改进和润饰，这些改进和润饰也应视为本申请的保护范围。

Claims (10)

  1. 一种可快速拆卸安装固定翼无人飞行器，其特征在于，包括机身主体、以及安装于机身主体上的机翼和尾部，所述尾部包括尾翼以及固定在机身主体和尾翼之间的尾杆，所述机身主体上设有一尾杆通道，所述尾杆的一端安装于所述尾杆通道内，所述尾杆插置于所述尾杆通道内的深度可调。
  2. 根据权利要求1所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述尾杆通道贯穿所述机身主体。
  3. 根据权利要求1所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述机身主体包括骨架以及安装于骨架外侧的壳体，所述骨架包括一水平设置的支撑板，所述支撑板的两侧对称安装有加强板，所述加强板与支撑板垂直设置，所述支撑板的上方安装有固定支架，所述尾杆通道形成于所述固定支架与支撑板之间。
  4. 根据权利要求3所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述固定支架上开设有固定孔，所述支撑板上设有螺孔，所述尾杆上开设有通孔，所述的固定孔、螺孔和通孔上下对应。
  5. 根据权利要求3所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述支撑板上开设有多个减重孔。
  6. 根据权利要求3所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述支撑板的前端固定有一挂机板，所述挂机板垂直支撑板设置，所述挂机板上开设有用以悬挂航拍相机的悬挂孔，所述挂机板的外侧遮盖有头罩，所述头罩与机身主体之间可拆卸安装。
  7. 根据权利要求1所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述机身主体的上方凹设形成有一伞仓空间，所述伞仓空间的上方遮盖有伞仓盖，所述伞仓盖与机身主体之间可拆卸固定。
  8. 根据权利要求1所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述机身主体的下方向上凹设形成有一挂机空间，该挂机空间的开口处遮盖有底仓盖，所述底仓盖与机身主体之间可拆卸固定。
  9. 根据权利要求1所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述机翼包括中段机翼、左段机翼和右段机翼，所述中段机翼固定于所述机身主体上，所述左段机翼和右段机翼分别可拆卸安装于中段机翼的左右 两侧，所述左段机翼和右段机翼的端部分别延伸有导杆，所述中段机翼的端部设有容纳所述导杆的安装孔，所述导杆包括并列设置的第一导杆和第二导杆，所述第一导杆的直径和延伸长度均大于所述第二导杆，所述第二导杆的直径沿背离所述左段机翼或右段机翼的方向逐渐减小，所述左段机翼与中段机翼之间、以及右段机翼与中段机翼之间分别固定有限制相邻机翼间相对移动的卡扣，所述卡扣包括从中部折弯形成的两个弹性臂，该两个弹性臂于相对位置相向凹设形成有卡持部，所述卡持部具有弧形表面，所述两个弹性臂的末端分别向外折弯形成有延伸臂，所述两个延伸臂之间呈八字形开口，所述中段机翼两侧的端面上分别固定有第一安装板，所述左段机翼和右段机翼的端面上固定有第二安装板，所述第一安装板和第二安装板上于对应位置上分别设有卡孔或卡槽，所述中段机翼、左段机翼和右段机翼上分别设有供所述卡扣弹性臂插入的插入口，所述插入口贴近所述第一安装板或第二安装板设置。
  10. 根据权利要求1所述的可快速拆卸安装固定翼无人飞行器，其特征在于：所述机翼的两侧在对称位置上分别安装有一旋翼，所述每个旋翼分别通过一电机驱动，所述电机的后方形成有一散热通道，所述散热通道位于所述机翼的下方，其中一所述散热通道内安装有天线；所述天线在水平方向和垂直方向之间可转动。
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