WO2019061100A1 - 机翼组件及无人飞行器 - Google Patents

机翼组件及无人飞行器 Download PDF

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Publication number
WO2019061100A1
WO2019061100A1 PCT/CN2017/103754 CN2017103754W WO2019061100A1 WO 2019061100 A1 WO2019061100 A1 WO 2019061100A1 CN 2017103754 W CN2017103754 W CN 2017103754W WO 2019061100 A1 WO2019061100 A1 WO 2019061100A1
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WO
WIPO (PCT)
Prior art keywords
wing
assembly
locking
fuselage
coupled
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PCT/CN2017/103754
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English (en)
French (fr)
Inventor
王坤殿
陈锦熙
胡奔
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN201780005697.3A priority Critical patent/CN108513557A/zh
Priority to PCT/CN2017/103754 priority patent/WO2019061100A1/zh
Publication of WO2019061100A1 publication Critical patent/WO2019061100A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft

Definitions

  • the invention relates to the technical field of drones, in particular to a foldable wing assembly and an unmanned aerial vehicle.
  • the UAV For the fixed-wing UAV, usually due to the long wing, the UAV is occupied by a large volume. In the process of storage or transportation, a large carrier is needed to package the UAV, which is not convenient for packaging and transport.
  • the present invention proposes a foldable wing assembly and an unmanned aerial vehicle to solve the above technical problems.
  • a wing assembly comprising: a first wing, a second wing, and a connection for connecting the first wing to an airframe of the unmanned aerial vehicle a mechanism, the first wing includes a first end and a second end opposite the first end, the connecting mechanism is assembled to the first end, and the second wing is detachably assembled Said second end;
  • first wing is rotatably coupled to the fuselage through the connecting mechanism to expand or fold the first wing relative to the fuselage.
  • an unmanned aerial vehicle comprising: a fuselage, and the wing assembly of any one of the above, the wing assembly being rotatably coupled to the fuselage, Expanded or folded relative to the body.
  • the invention designs a foldable wing assembly and an unmanned aerial vehicle therewith.
  • the wing assembly is divided into a detachably assembled multi-segment structure wing, and the wing connected to the fuselage is rotatably connected to make the machine
  • the multi-segment wing is detachably assembled, and the wing connected to the fuselage can be folded relative to the fuselage, so that the wing assembly is occupied in a non-used state with a small size for storage and carry.
  • FIG. 1 is a schematic overall structural view of an unmanned aerial vehicle according to an exemplary embodiment of the present invention
  • FIG. 2 is a schematic structural view showing a detachable wing assembly of an unmanned aerial vehicle according to an exemplary embodiment of the present invention
  • FIG. 3 is a schematic structural view of a wing of a UAV folded relative to a fuselage according to an exemplary embodiment of the present invention
  • FIG. 4 is a schematic structural view of a first wing folded relative to a fuselage in an unmanned aerial vehicle according to still another exemplary embodiment of the present invention
  • FIG. 5 is a schematic structural view of a connecting mechanism in a wing assembly according to an exemplary embodiment of the present invention
  • FIG. 6 is a schematic structural view of a first wing and a second wing connecting portion of a wing assembly according to an exemplary embodiment of the present invention
  • Figure 7 is an enlarged view of a portion B of Figure 6;
  • Figure 8 is an enlarged view of a portion A in Figure 3;
  • FIG. 9 is a schematic structural view of a tail fin of an unmanned aerial vehicle according to an exemplary embodiment of the present invention.
  • the wing assembly 10 of the embodiment of the present invention includes a first wing 11, a second wing 12, and a fuselage for connecting the first wing 11 to the unmanned aerial vehicle 100.
  • the first wing 11 can be folded and folded relative to the body 101 by the connecting mechanism 13, so that the volume occupied by the entire unmanned aerial vehicle 100 can be reduced to facilitate storage and carrying.
  • the first wing 11 includes a first end 111 and a second end 112 opposite the first end 111.
  • the connecting mechanism 13 is mounted on the first end 111
  • the second wing 12 is detachably mounted on the second end. End 112.
  • the first wing 11 is rotatably coupled to the body 101 by a connecting mechanism 13 to cause the first wing 11 to be unfolded or folded relative to the body 101.
  • the wing assembly 10 is in use; when the first wing 11 is folded relative to the fuselage 101, the wing assembly 10 is now in a non-use state.
  • the wing assembly 10 is not limited to the first wing 11 and the second wing 12.
  • the wing assembly 10 may further include a third wing, a fourth wing, and the like. The connection between the wings is the same as that of the first wing 11 and the second wing 12.
  • the connecting mechanism 13 includes a first connecting member 131 fixed to the body 101, and a second connecting member 132 fixed to the first end 111.
  • the second connecting member 132 is pivotally connected to The first connecting member 131 is configured to rotate the second connecting member 132 relative to the first connecting member 131.
  • the first connecting member 131 can be fixed to the body 101 by screws, rivets or a snap fit.
  • the second connecting member 132 can also be fixed to the first by screws, rivets or snaps.
  • the end surface of the first end 111 of the wing 11 is connected to the second connecting member 132 via a rotating shaft.
  • the first wing 11 is rotated downward (bottom direction) by the connecting mechanism 13 to be folded relative to the body 101, and when the first wing 11 is switched to the non-use state, the first wing 11 can be utilized.
  • the self-gravity is such that the wing is folded relative to the fuselage 101.
  • the first wings 11 on both sides of the body 101 are respectively attached to both sides of the body 101, so that the wing assembly 10 is in a non-use state.
  • the volume occupied by the time is small.
  • the limitation of the first wing 11 by the fuselage 101 can limit the rotation angle of the first wing 11 relative to the body 101.
  • the first wing 11 can also be rotated upward (top direction) by the connecting mechanism 13 to be rotated and folded relative to the body 101.
  • the first wing 11 can be deployed relative to the body 101 by its own gravity to be in use.
  • the first wing 11 can also be rotated and folded by the connecting mechanism 13 in the forward (head direction) relative to the body 101 or backwardly (in the direction of the tail 20), in particular, according to the configuration of the shape of the body 101. set.
  • the first wing 11 further includes a mating portion (not shown) provided at the first end 111.
  • the body 101 is further provided with a lock fitting (not shown).
  • the mating portion when the second wing body 101 of the first wing 11 is unfolded, the mating portion cooperates with the lock fitting on the body 101, and the lock fitting can also provide a supporting force for the first wing 11 to enhance the first machine.
  • the mating portion may be disposed in the body 101, and the lock fitting is disposed at the first end 111.
  • the lock fitting may be a carbon tube, and the fitting portion is a connecting hole that cooperates with the carbon tube.
  • the locking fitting and the engaging portion can be matched in a manner similar to the manner in which the pin and the pin hole are matched.
  • the carbon tube is disposed on the body 101 and can be moved into the mating portion or the mating portion to be relatively adjusted to fix the first wing 11 In the body 101.
  • the carbon tube can also be inserted into the fuselage 101 for simultaneously fitting to the first wing 11 on both sides. When assembling, the position of the carbon tube is moved to fix the first wing 11 on both sides.
  • the carbon tube is disposed on the first wing 11, and the connecting hole is disposed in the body 101.
  • the first tube is inserted into the connecting hole to achieve the first
  • the wing 11 is fixed to the body 101.
  • the carbon tube can also penetrate the first wing 11 so that the second wing 12 can be fixed to the first wing 11 through the carbon tube, and then the first wing 11 is fixed to the body 102.
  • the lock fitting and the structure of the fitting portion of the present invention are not limited thereto, and other lock fittings and fitting portions that can be used to hold the first wing 11 relative to the body 101 are suitable for use in embodiments of the present invention.
  • a communication cable (not shown) is also connected between the first wing 11 and the body 101 to allow the wing assembly 10 to be communicably coupled to the body 101.
  • the communication cable can not only provide communication between the wing assembly 10 and the fuselage 101 but also provide power to the wing assembly 10.
  • the communication cable has a certain amount of redundancy between the first wing 11 and the fuselage 101.
  • the communication cable may be an FPC (Flexible Printed Circuit) line or a coaxial line.
  • the wing assembly 10 further includes a first electrical connector (not shown) disposed at the second end 112, and the second wing 12 is provided with the first electrical connector.
  • the second electrical connector 121 is connected.
  • the first electrical connector is coupled to the second electrical connector 121 such that the second wing 12 is communicatively coupled to the first wing 11 .
  • the first connector and the second connector 121 are used, the first connector and the second connector 121 have a fixed connection effect, and the second wing 12 can be connected to the first On the wing 11.
  • the first wing 11 and the second wing 12 are respectively provided with steering gears 113 for controlling the rudder surfaces on the first wing 11 and the second wing 12, so that the unmanned aerial vehicle 100 can be controlled.
  • the first connector and the second connector 121 are coupled to the aeronautical connection male connector and the aviation connection female connector to implement communication between the first wing 11 and the second wing 12.
  • the first connector and the second connector 121 of the present invention are not limited to the use of an aeronautical connection male and an air connection female, and other types of connectors are also suitable for use in the present invention.
  • the wing assembly 10 also includes a locking mechanism disposed at the second end 112, and the second wing 12 is provided with a locking portion 122 that mates with the locking mechanism.
  • the locking mechanism is locked to the locking portion 122 to lock the second wing 12 to the first wing 11 .
  • the rigidity of the connection between the first wing 11 and the second wing 12 can be further ensured by the locking mechanism being engaged with the locking portion 122.
  • the locking mechanism can also be disposed on the second wing 12 , and the locking portion 122 is disposed at the second end 112 .
  • the locking mechanism includes a slider that is limited to the slot in the first end 111 141, a locking hook 142 connected to the sliding member 141, an elastic member 143 sleeved on the sliding member 141, and an adjusting member 144 connected to the sliding member 141.
  • the adjusting member 144 extends from the sliding slot.
  • the elastic member 143 is in the initial state
  • the locking hook 142 is in a state of being locked to the locking portion 122.
  • the sliding member 141 adjusts the adjusting hook 142 in the width direction of the first wing 11 to adjust the locking hook 142 to the locking portion 122 or to the locking portion 122; the sliding member 141 is restored in the elastic member 143. Under the force, the locking hook 142 is driven to lock the locking portion 122.
  • a side of the second wing 12 opposite to the second end 112 is further provided with a guiding rod (not shown), and the end surface of the second end 112 is correspondingly provided with a guiding hole (not shown), so that the first The two wings 12 are matched to the assembled position of the first wing 11.
  • the connection of the guiding rod to the guiding hole can provide strength for the second wing 12 to be connected to the first wing 11 and enhance the rigidity of the connection of the second wing 12 to the first wing 11.
  • the wing assembly 10 further includes a rotor assembly 15 disposed on the first wing 11 for providing flight power to the unmanned aerial vehicle 100, which can cause the UAV 100 to take off and land vertically.
  • the rotor assembly 15 includes a wing arm 151 coupled to the first wing 11, a power assembly 152 coupled to the two free ends of the wing arm 151, and a propeller 153 coupled to the power assembly 152, respectively.
  • the wing arm 151 is adjacent to the second end 112 of the first wing 11 , and the second end 112 is provided with a locking portion for fixing the wing arm 151 .
  • the axial direction of the wing arm 151 and the nose of the UAV 100 The direction toward the tail is the same.
  • a wire passage (not shown) is disposed in the wing arm 151 for receiving a cable connected to the power component and the first wing 11 to provide power for the power component through the circuit in the first wing 11 .
  • the cable further includes a communication cable, and the connection of the communication cable enables the body 101 to acquire information such as the rotation speed of the propeller.
  • the present invention contemplates a foldable wing assembly that is divided into detachably assembled multi-segmented wings and that is rotatably coupled to the fuselage to allow the wing assembly to be in a non-use state
  • the multi-segment wing is detachably assembled, and the wing connected to the fuselage can be folded relative to the fuselage, so that the wing assembly is occupied in a non-used state with a small size for storage and carrying. band.
  • an unmanned aerial vehicle 100 comprising: a fuselage 101, and as in any of the above embodiments
  • the wing assembly 10 is rotatably coupled to the body 101 for deployment or folding relative to the body 101.
  • the UAV 100 further includes a tail fin 20 coupled to the body 101.
  • the tail fin 20 includes a tail body 21 and a connecting arm 22 coupled to the tail body 21, and the body 101 is provided.
  • the empennage 20 is detachably fitted to the body 101 by the cooperation of the connecting arm 22 and the connecting portion 102, so that the volume occupied by the unmanned aerial vehicle 100 can be further reduced, which is convenient.
  • the user stores and carries, and the disassembly and assembly is simple and convenient.
  • the connecting arm 22 is provided with a locking pin 23, and the connecting portion 102 is provided with a locking hole 1021 for engaging with the locking pin 23.
  • the tail pin 20 is fixed to the body 101 by the cooperation of the lock pin 23 and the lock fitting hole 1021.
  • the lock pin 23 is an elastic structure, and the lock pin 23 includes a pin shaft and a spring that is fitted to the pin shaft. In the initial state, the spring can drive the pin shaft to protrude from the link arm 22 under its own elastic force.
  • the pin is retracted into the connecting arm 22 by pressing the pin shaft, and the spring is in a compressed state, so that the connecting arm 22 can be fitted into the connecting portion 102.
  • the pin shaft corresponds to the lock matching hole 1021
  • the pin shaft protrudes from the connecting arm 22 under the elastic restoring force of the spring, and is inserted into the locking matching hole 1021, so that the tail fin 20 is locked to the body 101.
  • the user presses the pin to release the pin from the locking hole 1021, thereby disassembling the tail 20 from the body 101.
  • This type of fitting can be assembled quickly and easily without the use of tools. Disassembled.
  • the connecting arm 22 is further provided with a third electrical connector (not shown) connected to the tail body 21, and the body 101 is provided with a fourth electrical connector (not shown) adapted to the third electrical connector (not shown).
  • the tail 20 is communicably connected to the body 101 while being assembled to the body 101.
  • the tail 20 is provided There is a steering gear 211 for cooperating with controlling the flight of the unmanned aerial vehicle 100.
  • communication is achieved by the third electrical connector and the fourth electrical connector such that the control module within the fuselage 101 controls the tail 20 to cooperate in flight.
  • the third electrical connector and the fourth electrical connector are connected by an air connection male and an air connection female.
  • the UAV 100 further includes two cradle 104 disposed on both sides of the body 101.
  • the two cradle 104 cooperate to support the body 101.
  • the maximum occupied size between the first wings 11 on both sides is not greater than the maximum occupied size of the two stands 104, so that the stand 104 is provided. The effect of protecting the first wing 11 can be achieved.
  • the assembly order of the wing assembly 10 and the empennage 20 is not limited, and the wing assembly 10 may be assembled first or the empennage 20 may be assembled first.
  • the first wing 11 When the wing assembly 10 is assembled, the first wing 11 can be first rotated by the connecting mechanism 13 to be unfolded relative to the body 101, and then inserted into the mating portion through the lock fitting to fix the first wing 11 and then
  • the second wing 12 is mounted on the first wing 11 and can be pre-positioned in the guiding hole of the second end 112 through the guiding rod on the second wing 12, and the first connector is connected to the second connector correspondingly.
  • the device 121 is docked, and then cooperates with the lock portion 122 by the locking mechanism 13 to further fix the second wing 12 to the first wing 11; of course, the second wing 12 can also be first assembled to the first wing 11 Then, the first wing 11 is unfolded relative to the body 101, and the assembly manner is the same as that of the above embodiment, only in the difference in the assembly order.
  • the second wing 12 is turned by the adjustment member 144 of the locking mechanism 13 to unlock the locking hook 142 and the locking portion 122, and then the second wing 12 is away from the first wing 11
  • the second wing 11 is detached from the first wing 11, the first connector and the second connector 121 are loosened, the guiding rod is also pulled out from the guiding hole, and the second wing 12 is detached from the first wing 11.
  • the lock fitting is then adjusted to disengage the lock fitting from the first wing 11, at which point the first wing 11 is folded relative to the fuselage 101 under its own weight so that the first wing 11 is in close proximity to the fuselage 101.
  • the lock pin 23 is pressed to retract the lock pin 23 into the connecting arm 22, and Then, the connecting arm 22 is inserted into the connecting portion 102 of the body 101, and the third connector and the fourth connector are connected correspondingly, and the locking pin 23 is corresponding to the locking hole 1021 on the connecting portion 102.
  • the locking pin 23 is popped into the locking matching hole 1021 to realize a fixed connection and a communication connection of the tail 20 to the body 101.
  • the invention designs an unmanned aerial vehicle having a foldable wing assembly, the wing assembly being divided into detachably assembled multi-segment structure wings, and the wing connected to the fuselage is rotatably connected to The wing assembly is detachably assembled in a non-use state, and the wing connected to the fuselage can be folded relative to the fuselage, so that the wing assembly is occupied in a non-used state with a small size for storage. And carry.
  • the UAV has a tail that can be quickly disassembled and connected, and can be quickly disassembled through the tail, which can further reduce the occupation size of the UAV.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)

Abstract

一种机翼组件（10）及无人飞行器（100），该机翼组件（10）包括：第一机翼（11）、第二机翼（12）、以及用于将第一机翼（11）连接于无人飞行器（100）的机身（101）的连接机构（13），第一机翼（11）包括第一端（111）以及与第一端（111）相背的第二端（112），连接机构（13）装配于第一端（111），第二机翼（12）可拆卸地装配于第二端（112）；其中，第一机翼（11）通过连接机构（13）转动连接于所述机身（101），以使所述第一机翼（11）相对所述机身（101）展开或者折叠。机翼组件分为可拆卸装配的多段结构机翼，而且与机身相连的机翼可以相对机身折叠，从而使机翼组件在非使用状态下所占用的尺寸较小，以便于存放及携带。

Description

机翼组件及无人飞行器 技术领域
本发明涉及无人机技术领域，特别涉及一种可折叠的机翼组件及无人飞行器。
背景技术
随着科学技术的飞速发展，无人飞行器技术发展越来越成熟，应用的领域也越来越广泛，例如：军事、科研、民用等领域，具体可以用于摄影、勘探、通信、防灾减灾、边境巡逻等等。
针对固定翼的无人飞行器，通常由于机翼较长，导致无人飞行器整体所占用的体积较大，在存放或者运输过程中，需要较大的载体来包装该无人飞行器，不便于包装及运输。
发明内容
本发明提出一种可折叠的机翼组件及无人飞行器以解决上述技术问题。
根据本发明实施例的第一方面，提供了一种机翼组件，包括：第一机翼、第二机翼、以及用于将所述第一机翼连接于无人飞行器的机身的连接机构，所述第一机翼包括第一端以及与所述第一端相背的第二端，所述连接机构装配于所述第一端，所述第二机翼可拆卸地装配于所述第二端；
其中，所述第一机翼通过所述连接机构转动连接于所述机身，以使所述第一机翼相对所述机身展开或者折叠。
根据本发明实施例的第二方面，提供了一种无人飞行器，包括：机身、以及如上述中任一项所述的机翼组件，所述机翼组件转动连接于所述机身，以相对所述机身展开或者折叠。
本发明设计了一种可折叠的机翼组件及具有其的无人飞行器，该机翼组件分为可拆卸装配的多段结构机翼，且与机身连接的机翼可转动连接，以使机翼组件在非使用状态下，多段机翼可拆卸装配，而且与机身相连的机翼可以相对机身折叠，从而使机翼组件在非使用状态下所占用的尺寸较小，以便于存放及携带。
附图说明
为了更清楚地说明本发明实施例中的技术方案，下面将对实施例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发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。
图1是本发明一示例性实施例示出的一种无人飞行器的整体结构示意图；
图2是本发明一示例性实施例示出的一种无人飞行器的机翼组件可拆装的结构示意图；
图3是本发明一示例性实施例示出的一种无人飞行器中机翼相对机身折叠的结构示意图；
图4是本发明又一示例性实施例示出的一种无人飞行器中第一机翼相对机身折叠的结构示意图；
图5是本发明一示例性实施例示出的一种机翼组件中连接机构的结构示意图；
图6是本发明一示例性实施例示出的一种机翼组件第一机翼与第二机翼连接部分的结构示意图；
图7是图6中B部分的放大图；
图8是图3中的A部分的放大图；
图9是本发明一示例性实施例示出的一种无人飞行器的尾翼的结构示意图。
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清楚、完整地描述，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。
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。
在本发明使用的术语是仅仅出于描述特定实施例的目的，而非旨在限制本发明。在本发明和所附权利要求书中所使用的单数形式的“一种”、“所述”和“该”也旨在包括多数形式，除非上下文清楚地表示其他含义。还应当理解，本文中使用的术语“和/或”是指并包含一个或多个相关联的列出项目的任何或所有可能组合。
下面结合附图，对本发明无人飞行器进行详细说明。在不冲突的情况下，下述的实施例及实施方式中的特征可以相互组合。
如图1至图5所示，本发明实施例的机翼组件10包括：第一机翼11、第二机翼12、以及用于将第一机翼11连接于无人飞行器100的机身101的连接机构13。该第一机翼11可以通过连接机构13相对机身101折叠收起，从而可以减少整个无人飞行器100所占用的体积空间，以便于存放及携带。
具体地，该第一机翼11包括第一端111以及与第一端111相背的第二端112，连接机构13装配于第一端111，第二机翼12可拆卸地装配于第二端112。在本发明中，第一机翼11通过连接机构13转动连接于机身101，以使第一机翼11相对机身101展开或者折叠。当第一机翼11相对机身101展开时，该机翼组件10处于使用状态；当第一机翼11相对机身101折叠时，此时机翼组件10处于非使用状态。本发明中，机翼组件10并不限于第一机翼11和第二机翼12，根据无人飞行器100的尺寸设计，机翼组件10还可以包括第三机翼、第四机翼等，该些机翼之间的连接与第一机翼11和第二机翼12的连接方式相同。
如图3至图5所示，该连接机构13包括固定于机身101的第一连接件131、以及固定于第一端111的第二连接件132，该第二连接件132枢轴连接于第一连接件131，以使该第二连接件132可以相对第一连接件131转动。该实施例中，第一连接件131可以通过螺钉、铆钉或者卡配等方式固定在机身101上，同样地，第二连接件132也可以通过螺钉、铆钉或者卡配等方式固定在第一机翼11的第一端111的端面，第一连接件131与第二连接件132通过转轴连接。
在本实施例中，第一机翼11通过连接机构13向下(机底方向)转动以相对机身101折叠，在第一机翼11转换为非使用状态时，可以利用第一机翼11的自身重力以使机翼相对机身101折叠。该实施例中，当第一机翼11相对机身101折叠时，机身101两侧的第一机翼11分别贴合在机身101两侧，如此以使机翼组件10处于非使用状态时所占用的体积空间较小。 其中，通过机身101对第一机翼11的限位，可以限制第一机翼11相对机身101的转动角度。
当然，在本发明的其他实施例中，根据无人飞行器100的机型的不同，该第一机翼11还可以通过连接机构13向上(机顶方向)转动以相对机身101转动折叠，该第一机翼11可以利用自身重力相对机身101展开以处于使用状态。另外，该第一机翼11还可以通过连接机构13以相对机身101向前(机头方向)转动折叠或者向后(尾翼20方向)转动折叠，具体地可以根据机身101形状的构成而定。
进一步地，第一机翼11还包括设于第一端111的配合部(未图示)，相对应地，机身101上还设有锁配件(未图示)。其中，在第一机翼11第二相对机身101展开时，配合部与机身101上的锁配件配合锁定，该锁配件还可以为第一机翼11提供支撑力，以增强第一机翼11与机身101的连接强度。当然，也可以将配合部设于机身101，锁配件设于第一端111。
在一可选实施例中，该该锁配件可以为碳管，配合部为与碳管配合的连接孔。该锁配件与配合部的配合方式可以与插销及销孔的配合方式类似，碳管设于机身101上，可以被相对调节地移入配合部或者移出配合部，以使第一机翼11固定于机身101。其中，该碳管还可以贯穿于机身101用以同时配合于两侧的第一机翼11，在装配时，通过移动碳管的位置以使两侧的第一机翼11进行固定装配。
在又一实施例中，碳管设于第一机翼11上，连接孔设于机身101，在第一机翼11相对机身101展开时，通过将碳管插入连接孔以实现第一机翼11与机身101的固定。其中，该碳管还可以贯穿第一机翼11，以使通过该碳管可以将第二机翼12固定于第一机翼11，而后将第一机翼11固定于机身102。当然，本发明的锁配件及配合部的结构并不限于此，其他可以用于将第一机翼11保持相对与机身101展开的锁配件和配合部均适用于本发明的实施例中。
该第一机翼11与机身101之间还连接有通信线缆(未图示)，以使机翼组件10可以通信连接于机身101。优选地，该通信线缆不仅可以实现机翼组件10与机身101之间的通信而且还可以为机翼组件10提供电源。为了避免通信线缆影响机翼组件10相对应机身101的折叠，该通信线缆在第一机翼11与机身101之间具有一定冗余量。其中，该通信线缆可以为FPC(Flexible Printed Circuit，柔性电路板)线或者同轴线。
如图1、图6和图7所示，该机翼组件10还包括设于第二端112的第一电连接器(未图示)，第二机翼12设有与第一电连接器配合连接的第二电连接器121。其中，在第二机翼12装配于第一机翼11时，将第一电连接器与第二电连接器121配合连接，以使第二机翼12与第一机翼11通信连接。在使用刚性较强的第一连接器与第二连接器121时，该第一连接器与第二连接器121配合连接还具有固定连接的效果，可以使第二机翼12连接到该第一机翼11上。
在本发明中，第一机翼11和第二机翼12内分别设有舵机113，用以控制第一机翼11和第二机翼12上的舵面，从而可以控制无人飞行器100的飞行方向。本实施例中，该第一连接器与第二连接器121选用航空连接公头和航空连接母头配合连接，以实现第一机翼11与第二机翼12之间的通信。当然，本发明的第一连接器与第二连接器121并不限于选用航空连接公头和航空连接母头，其他类型的连接器也适用于本发明中。
机翼组件10还包括设于第二端112的锁定机构，第二机翼12设有与锁定机构配合的锁配部122。其中，在第二机翼12装配于第一机翼11时，通过锁定机构锁扣于锁配部122，以使第二机翼12锁定于第一机翼11。本实施例中，通过锁定机构与锁配部122配合可以进一步保证第一机翼11与第二机翼12的连接刚性。当然，在另一实施例中，该锁定机构也可以设于第二机翼12，锁配部122设于第二端112。
在实施例中，锁定机构包括限位于第一端111的滑槽内的滑动件 141、连接于滑动件141的锁钩142、套设于滑动件141上的弹性件143、以及连接于滑动件141上的调节件144。该调节件144从滑槽内延伸出，弹性件143处于初始状态时，锁钩142处于锁扣于锁配部122的状态。其中，滑动件141在调节件144沿第一机翼11的宽度方向上的调节下，调控锁钩142装配于锁配部122或者解锁于锁配部122；滑动件141在弹性件143的回复力下，驱使锁钩142锁扣于锁配部122。
进一步地，该第二机翼12与第二端112相对的一侧面还设有导向杆(未图示)，第二端112的端面上对应设有导向孔(未图示)，以使第二机翼12匹配于第一机翼11的装配位置。该实施例中，通过导向杆与导向孔的连接，可以为第二机翼12连接于第一机翼11提供强度，增强第二机翼12与第一机翼11连接的刚性。
如图1和图2所示，机翼组件10还包括设于第一机翼11上的旋翼组件15，用于为无人飞行器100提供飞行动力，可以使无人飞行器100垂直起降。具体地，该旋翼组件15包括连接于第一机翼11上的翼臂151、分别连接于所述翼臂151的两个自由端的动力组件152、以及连接于所述动力组件152上的螺旋桨153。其中，该翼臂151靠近第一机翼11的第二端112，该第二端112设有用以固定该翼臂151的卡持部，翼臂151的轴向与无人飞行器100的机头朝向机尾的方向一致。
进一步地，该翼臂151内设有线路通道(未图示)，用以容纳连接于动力组件与第一机翼11的线缆，从而通过第一机翼11内的电路为动力组件提供电源。另外，该线缆还包括通信线缆，通过通信线缆的连接可以使机身101获取螺旋桨的转速等信息。
本发明设计了一种可折叠的机翼组件，该机翼组件分为可拆卸装配的多段结构机翼，且与机身连接的机翼可转动连接，以使机翼组件在非使用状态下，多段机翼可拆卸装配，而且与机身相连的机翼可以相对机身折叠，从而使机翼组件在非使用状态下所占用的尺寸较小，以便于存放及携 带。
如图1至图3所示，根据本发明实施例的又一方面，还提供了一种无人飞行器100，该无人飞行器100包括：机身101、以及如上述实施例中任一项所述的机翼组件10，该机翼组件10转动连接于所述机身101，以相对机身101展开或者折叠。具体地的连接方式及结构特征请参照上述实施例所示，在此就不再重复赘述。
如图3、图8和图9所示，无人飞行器100还包括连接于机身101的尾翼20，尾翼20包括尾翼主体21、以及连接于尾翼主体21的连接臂22，机身101上设有与连接臂22配合连接的连接部102。本实施例中，该尾翼20通过连接臂22和连接部102的配合，以使尾翼20可拆卸地装配于机身101上，从而可以进一步地减少该无人飞行器100所占用的体积空间，便于用户存放及携带，而且拆卸及装配较为简捷，使用方便。
进一步地，该连接臂22上设有锁销23，连接部102上设有与锁销23配合的锁配孔1021。其中，通过锁销23与锁配孔1021的配合，以将尾翼20固定于机身101。具体地，该锁销23为弹性结构，该锁销23包括销轴以及配合于销轴的弹簧，在初始状态时，弹簧在自身弹性力下可以驱使该销轴凸伸出连接臂22。当用户需要将该尾翼20安装于机身101时，通过按压该销轴以使销轴缩入连接臂22内，此时弹簧处于压缩状态，从而可以使连接臂22装配于连接部102内。在该销轴对应到锁配孔1021时，销轴在弹簧的弹性回复力下，凸伸出连接臂22，进而插置于锁配孔1021内，从而实现尾翼20锁固于机身101。在拆卸该尾翼20时，同样地通过用户按压销轴，以使销轴退出锁配孔1021，从而实现尾翼20从机身101上拆卸，该种配合方式无需借助工具即可简单快捷地装配及拆卸。
其中，连接臂22上还设有与尾翼主体21连接的第三电连接器(未图示)，机身101上设有与第三电连接器适配的第四电连接器(未图示)，以使尾翼20装配于机身101的同时通信连接于机身101。该尾翼20中设 有舵机211，用以配合控制无人飞行器100的飞行。本实施例中，通过第三电连接器和第四电连接器实现通信，以使机身101内控制模块控制尾翼20配合飞行。可选地，该第三电连接器和第四电连接器选用航空连接公头和航空连接母头。
该无人飞行器100还包括设于机身101两侧的两个停机架104，两个停机架104配合用以供支撑机身101。优选地，在第一机翼11相对机身101折叠后，两侧第一机翼11的之间的最大占用尺寸不大于两个停机架104的最大占用尺寸，如此以使停机架104可以起到保护第一机翼11的效果。
本发明的无人飞行器100在组装时，机翼组件10与尾翼20的组装顺序并不限定，可以先组装机翼组件10也可以先组装尾翼20。
在组装机翼组件10时，可以先将第一机翼11通过连接机构13转动以相对机身101展开，而后通过锁配件插置于配合部以将第一机翼11固定住，接着将第二机翼12装配于第一机翼11上，可以预先通过第二机翼12上的导向杆装配于第二端112的导向孔内进行预定位，并对应将第一连接器与第二连接器121对接，而后通过锁定机构13与锁配部122配合以将第二机翼12进一步固定于第一机翼11上；当然，也可以先将第二机翼12装配于第一机翼11，而后再将第一机翼11相对机身101展开，该装配方式与上述实施例相同，仅在于装配顺序的不同。
机翼组件10拆卸时，通过拨动锁定机构13的调节件144以使锁钩142解锁与锁配部122，而后在第二机翼12远离第一机翼11方向上将第二机翼12从第一机翼11上拆卸下来，此时第一连接器与第二连接器121松脱，导向杆也从导向孔内拔出，第二机翼12从第一机翼11上拆卸下来，而后调节锁配件以使锁配件从第一机翼11上脱离出，此时第一机翼11在自身重力下相对机身101折叠，以使第一机翼11贴近于机身101。
在装配尾翼20时，按压锁销23以使锁销23缩入连接臂22内，而 后将连接臂22插置入机身101的连接部102内，并将第三连接器和第四连接器对应连接，同时使锁销23对应于连接部102上的锁配孔1021，此时锁销23弹起锁配于锁配孔1021内，从而实现尾翼20与机身101的固定连接和通信连接。在拆卸尾翼20时，通过按压锁销23以使锁销23解锁于锁配孔1021，此时将连接臂22朝向远离机身101的方向拔出，以使第三连接器与第四连接器拆分开，进而使连接臂22脱离于连接部102，从而完成尾翼20的拆卸。
本发明设计了一种无人飞行器，该无人飞行器具有可折叠的机翼组件，机翼组件分为可拆卸装配的多段结构机翼，且与机身连接的机翼可转动连接，以使机翼组件在非使用状态下，多段机翼可拆卸装配，而且与机身相连的机翼可以相对机身折叠，从而使机翼组件在非使用状态下所占用的尺寸较小，以便于存放及携带。另外，该无人飞行器还具有可快捷拆卸连接的尾翼，通过尾翼可快捷地拆卸，可以进一步地减小无人飞行器的占用尺寸。
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。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。
以上对本发明实施例所提供的方法和装置进行了详细介绍，本文中应用了具体个例对本发明的原理及实施方式进行了阐述，以上实施例的说明只是用于帮助理解本发明的方法及其核心思想；同时，对于本领域的一 般技术人员，依据本发明的思想，在具体实施方式及应用范围上均会有改变之处，综上所述，本说明书内容不应理解为对本发明的限制。
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Claims (14)

  1. 一种机翼组件，其特征在于，包括：第一机翼、第二机翼、以及用于将所述第一机翼连接于无人飞行器的机身的连接机构，所述第一机翼包括第一端以及与所述第一端相背的第二端，所述连接机构装配于所述第一端，所述第二机翼可拆卸地装配于所述第二端；
    其中，所述第一机翼通过所述连接机构转动连接于所述机身，以使所述第一机翼相对所述机身展开或者折叠。
  2. 根据权利要求1所述的机翼组件，其特征在于，所述连接机构包括固定于所述机身的第一连接件、以及固定于所述第一端的第二连接件；其中，所述第二连接件枢轴连接于所述第一连接件。
  3. 根据权利要求2所述的机翼组件，其特征在于，所述第一机翼还包括设于所述第一端的配合部；其中，在所述第一机翼相对所述机身展开时，所述配合部与所述机身上的锁配件配合锁定。
  4. 根据权利要求1所述的机翼组件，其特征在于，所述机翼组件还包括设于所述第二端的第一电连接器，所述第二机翼设有与所述第一电连接器配合连接的第二电连接器；
    其中，在所述第二机翼装配于所述第一机翼时，将所述第一电连接器与所述第二电连接器配合连接，以使所述第二机翼与所述第一机翼通信连接。
  5. 根据权利要求4所述的机翼组件，其特征在于，所述机翼组件还包括设于所述第二端的锁定机构，所述第二机翼设有与所述锁定机构配合的锁配部；
    其中，在所述第二机翼装配于所述第一机翼时，通过所述锁定机构锁扣于所述锁配部，以使所述第二机翼锁定于所述第一机翼。
  6. 根据权利要求5所述的机翼组件，其特征在于，所述锁定机构包括限位于第一端的滑槽内的滑动件、连接于所述滑动件的锁钩、套设于所述滑动件上的弹性件、以及连接于所述滑动件上的调节件，所述调节件从所述滑槽 内延伸出，所述弹性件处于初始状态时，所述锁钩处于锁扣于所述锁配部的状态；
    其中，所述滑动件在所述调节件沿所述第一机翼的宽度方向上的调节下，调控所述锁钩装配于所述锁配部或者解锁于所述锁配部；所述滑动件在所述弹性件的回复力下，驱使所述锁钩锁扣于所述锁配部。
  7. 根据权利要求4所述的机翼组件，其特征在于，所述第二机翼与所述第二端相对的一侧面还设有导向杆，所述第二端的端面上对应设有导向孔，以使所述第二机翼匹配于所述第一机翼的装配位置。
  8. 根据权利要求1所述的机翼组件，其特征在于，所述机翼组件还包括设于所述第一机翼上的旋翼组件，用于为所述无人飞行器提供飞行动力。
  9. 根据权利要求8所述的机翼组件，其特征在于，所述旋翼组件包括连接于所述第一机翼上的翼臂、连接于所述翼臂的自由端的动力组件、以及连接于所述动力组件上的螺旋桨。
  10. 根据权利要求9所述的机翼组件，其特征在于，所述翼臂内设有线路通道，用以容纳连接于所述动力组件与所述第一机翼的线缆。
  11. 一种无人飞行器，其特征在于，包括：机身、以及如权利要求1至10中任一项所述的机翼组件，所述机翼组件转动连接于所述机身，以相对所述机身展开或者折叠。
  12. 根据权利要求11所述的无人飞行器，其特征在于，所述无人飞行器还包括连接于机身的尾翼，所述尾翼包括尾翼主体、以及连接于所述尾翼主体的连接臂，所述机身上设有与所述连接臂配合连接的连接部。
  13. 根据权利要求12所述的无人飞行器，其特征在于，所述连接臂上设有锁销，所述连接部上设有与所述锁销配合的锁配孔；其中，通过所述锁销与所述锁配孔的配合，以将所述尾翼固定于所述机身。
  14. 根据权利要求12所述的无人飞行器，其特征在于，所述连接臂上还设有与所述尾翼主体连接的第三电连接器，所述机身上设有与所述第三电连接器适配的第四电连接器，以使所述尾翼装配于所述机身的同时通信连接于 所述机身。
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