WO2020135448A1 - 一种无人飞行器 - Google Patents

一种无人飞行器 Download PDF

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Publication number
WO2020135448A1
WO2020135448A1 PCT/CN2019/128059 CN2019128059W WO2020135448A1 WO 2020135448 A1 WO2020135448 A1 WO 2020135448A1 CN 2019128059 W CN2019128059 W CN 2019128059W WO 2020135448 A1 WO2020135448 A1 WO 2020135448A1
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WO
WIPO (PCT)
Prior art keywords
landing gear
contact surface
mounting plate
fuselage
unmanned aerial
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/CN2019/128059
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English (en)
French (fr)
Inventor
梁智颖
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.)
Autel Robotics Co Ltd
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Autel Robotics Co Ltd
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Filing date
Publication date
Application filed by Autel Robotics Co Ltd filed Critical Autel Robotics Co Ltd
Publication of WO2020135448A1 publication Critical patent/WO2020135448A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/26—Control or locking systems therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/60—Take-off or landing of UAVs from a runway using their own power

Definitions

  • the invention relates to the field of aircraft, and in particular to an unmanned aerial vehicle.
  • the landing gear as an attachment device for unmanned aerial vehicles with bearing and maneuverability, bears an extremely important mission during the safe takeoff and landing of the unmanned aerial vehicle, and is one of the important parts of the unmanned aerial vehicle.
  • the landing gear is generally fixed.
  • embodiments of the present invention provide an unmanned aerial vehicle equipped with a landing gear, which is easy to carry.
  • An unmanned aerial vehicle which includes a fuselage and a landing gear assembly mounted on the fuselage, the landing gear assembly includes: a landing gear, the landing gear may be relative to the fuselage about a centerline Rotation; compression structure, one end of the compression structure is connected to the rotating shaft, and the other end is connected to the fuselage, the compression structure is used to provide the landing gear close to the fuselage along the centerline
  • the pressing force of one of the fuselage and the landing gear is provided with a lock hole, and the other of the fuselage and the landing gear is provided with a lock pin;
  • the lock hole cooperates so that the position of the landing gear relative to the fuselage is locked; the lock pin can be separated from the lock hole so that the landing gear can be rotated around the center relative to the fuselage The line turns.
  • the fuselage is further provided with a mounting plate, one of the mounting plate and the landing gear is provided with the lock hole, and the mounting plate and the landing gear are both The other is provided with the lock pin.
  • the lock pin is provided on the landing gear, and the lock hole is provided on the mounting plate.
  • the mounting plate has a first contact surface
  • the landing gear has a second contact surface facing the first contact surface and in contact with the first contact surface
  • the locking pin is provided on the The first contact surface, and the lock pin extends along the center line toward the second contact surface, and the lock hole is formed on the second contact surface accordingly.
  • the lock hole is provided on the landing gear, and the lock pin is provided on the mounting plate.
  • the mounting plate has a first contact surface
  • the landing gear has a second contact surface facing the first contact surface and in contact with the first contact surface
  • the locking pin is provided on the The second contact surface, and the lock pin extends along the center line toward the first contact surface, and the lock hole is formed on the first contact surface accordingly.
  • the mounting plate is provided with a mounting groove
  • the second contact surface is a groove bottom of the mounting groove; one end of the landing gear provided with the first contact surface is received in the mounting groove Inside.
  • one of the landing gear and the fuselage is provided with a rotating shaft provided along the center line, and the other is provided with a shaft hole, and the rotating shaft is inserted into the shaft hole.
  • the rotating shaft is provided on the landing gear
  • the shaft hole is provided on the mounting plate
  • the shaft hole penetrates the mounting plate and communicates with the inside of the fuselage.
  • the pressing structure includes a pressing plate and an elastic member; the pressing plate is disposed at an end of the rotating shaft passing through the shaft hole, the elastic member is sleeved on the rotating shaft, and the elastic member resists It is connected between the pressing plate and the mounting plate.
  • the elastic member is a compression spring.
  • the pressure plate is screwed to the rotating shaft.
  • the unmanned aerial vehicle is configured with a landing gear assembly, and the landing gear in the landing gear assembly can be deployed relative to the fuselage or Folding can make the UAV easy to carry.
  • FIG. 1 is a perspective view of an unmanned aerial vehicle according to one embodiment of the present invention.
  • FIG. 2 is a cross-sectional view of the landing gear assembly of the UAV shown in FIG. 1, wherein the landing gear of the landing gear assembly is partially omitted;
  • FIG. 3 is a top view of the UAV shown in FIG. 1, in which parts of the UAV are omitted;
  • FIG. 4 is a front view of the UAV shown in FIG. 1, in which the length of the two wings is omitted;
  • FIG. 5 is a cross-sectional view of the landing gear assembly shown in FIG. 2 in another embodiment, in which the landing gear is partially omitted;
  • FIG. 6 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a first state
  • FIG. 7 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a second state
  • FIG. 8 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a third state
  • FIG. 9 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a fourth state.
  • an unmanned aerial vehicle 100 may be a multi-rotor drone, a fixed-wing drone, or a tilt-rotor drone.
  • the The unmanned aerial vehicle 100 is a tilt-rotor drone as an example for detailed description.
  • the UAV 100 has a symmetrical structure as a whole and has a plane of symmetry M.
  • the UAV 100 includes a fuselage 10, two wings 20, two sets of propeller assemblies 30, and a landing gear assembly 40. Wherein the two wings 20 are disposed on opposite sides of the fuselage 10, the two sets of propeller assemblies 30 are respectively disposed on the two wings 20, and the landing gear assembly 40 is disposed on the On the fuselage 10.
  • the fuselage 10 has a generally long shuttle shape and is symmetrical with respect to the symmetry plane M.
  • the body 10 is provided with a mounting plate 11 that can be detachably connected to the body 10, for example, by a threaded connection, the mounting plate 11 can also be connected to the body 10 One piece.
  • the mounting plate 11 has a flat plate shape as a whole, and has a mounting surface 110.
  • the mounting surface 110 is a surface of the mounting plate 11 facing away from the body 10.
  • the two wings 20 are distributed symmetrically with respect to the symmetry plane M.
  • the two sets of propeller assemblies 30 are symmetrically distributed with respect to the plane of symmetry M.
  • the two sets of propeller assemblies 30 can rotate relative to the two wings 20, for example, the two sets of propeller assemblies 30 rotate 90 degrees, In order to provide vertical upward lift, the UAV 100 can be lifted vertically.
  • the number of the landing gear assemblies 40 is two, and the two landing gear assemblies 40 are symmetrically distributed with respect to the symmetry plane M.
  • the landing gear assembly 40 includes a landing gear 42 and a pressing structure 43.
  • the landing gear 42 is mounted on the mounting plate 11.
  • the pressing structure 43 connects the mounting plate 11 and the starting structure. ⁇ 42 ⁇ 42.
  • the mounting plate 11 may be omitted, that is, the mounting surface 110 is directly disposed on the body 10.
  • the mounting surface 110 is provided with a mounting groove 111, the mounting groove 111 is a circular groove, one end of the landing gear 42 is received in the mounting groove 111, and a first contact surface 112 is provided on the bottom of the mounting groove 111 ,
  • the shaft hole 113 and the at least two lock holes 114 are both provided in the landing gear 42, the shaft hole 113 has a center line S, the shaft hole communicates with the inside of the body 10, the The shaft hole 113 and the at least two lock holes 114 are correspondingly formed with the first contact surface 112, that is, the shaft hole 113 and the at least two lock holes 114 are along the center line
  • the direction of S is recessed from the first contact surface 112.
  • the openings of the shaft hole 113 and the openings of the at least two lock holes 114 are both opened on the first contact surface.
  • the center line S and the symmetry plane M are set at a first angle a, the first angle a is an acute angle, so that the landing gear 42 is relative to the mounting plate 11
  • the opening and closing angle c of the landing gear 42 and the symmetry plane changes, so that the landing gear 42 can be unfolded or folded relative to the fuselage 10.
  • the opening and closing angle c is the maximum value; when the landing gear 42 is folded relative to the fuselage 10, the opening and closing angle c is the minimum value.
  • the opening at the first angle between the centerline S and the symmetry plane M is toward the tail of the fuselage 10, and when the UAV 100 is flying horizontally, the centerline The S level is set so that during the flight of the UAV, the air resistance to the landing gear is small.
  • the at least two lock holes 114 are distributed circumferentially around the center line S. Preferably, the at least two lock holes 114 are equally spaced. Any one of the at least two lock holes 114 may be a through hole or a blind hole, which is not limited in this embodiment.
  • any one of the at least two lock holes 114 is cylindrical.
  • any one of the at least two lock holes 114 is hemispherical.
  • the at least two lock holes 114 include a first lock hole and a second lock hole, and the first lock hole and the second lock hole are arranged symmetrically with respect to the center line S.
  • the landing gear 42 includes a supporting portion 420 and a connecting portion 421 extending at one end of the supporting portion 420.
  • the support portion 420 has a long column shape, and the support portion 420 is used to support the fuselage 10 when the landing gear 42 is unfolded relative to the fuselage 10.
  • the connecting portion 421 has a long column shape, the axis of the connecting portion 421 coincides with the center line S, the connecting portion 421 and the supporting portion 420 form a second angle b, and the second angle b Is an obtuse angle, so that when the landing gear 42 is deployed relative to the fuselage 10, the end of the support portion 420 closer to the connecting portion 421 is closer to the symmetry plane M than the end farther away from the connecting portion 421, That is, the support portions 420 of the two support frames 42 are in a figure eight shape, so that the stability of the landing gear 42 to support the fuselage 10 is improved.
  • the second angle b is greater than or equal to the supplementary angle of the first angle a, that is, the second angle b is greater than or equal to the difference between 180 degrees and the first angle a, so that When the landing gear 42 is folded relative to the fuselage 10, the end of the supporting portion 420 closer to the connecting portion 421 is closer to the tail portion of the fuselage 10 than the end farther away from the connecting portion 421, so that the support The portion 420 is parallel or tends to be parallel to the symmetry plane M.
  • An end of the connecting portion 421 facing away from the supporting portion 420 is provided with a second contact surface 423.
  • the second contact surface 423 faces the first contact surface 112, and a rotating shaft 424 and a locking pin 425 are provided on the second contact surface 423.
  • the rotating shaft 424 and the locking pin 425 both extend along the center line S toward the second contact surface 423.
  • the rotating shaft 424 is adapted to the shaft hole 113, and the rotating shaft 424 is used to be inserted into the shaft hole 113.
  • the positions of the rotating shaft 424 and the shaft hole 113 can be interchanged, that is, the rotating shaft 424 is disposed on the first contact surface 112, and the shaft hole 113 is disposed on the first
  • the rotating shaft 424 is disposed on the first contact surface 112
  • the shaft hole 113 is disposed on the first
  • the two contact surfaces 423 as long as one of the first contact surface 112 and the second contact surface 423 is provided with the shaft hole 113, the other is provided with the rotating shaft 424.
  • the lock pin 425 is adapted to any one of the at least two lock holes 114.
  • the lock pin 425 is used to be inserted into any one of the at least two lock holes 113.
  • the positions of the lock pin 425 and the at least two lock holes 114 can be interchanged, that is, the lock pin 425 is disposed on the first contact surface 112, and the at least two The lock hole 114 is provided on the second contact surface 423 as long as one of the first contact surface 112 and the second contact surface 123 is provided with the lock pin 425 and the other is provided with the at least two A keyhole 114 is sufficient.
  • the lock pin 425 includes a first lock pin and a second lock pin, the first lock pin is used to insert into one of the first lock hole and the second lock hole, and the second lock pin is used to Insert the other of the first lock hole and the second lock hole.
  • the first locking pin is inserted into the first locking hole
  • the second locking pin is inserted into the second locking hole; when the second locking pin is inserted into the second locking hole, the second The lock pin is inserted into the first lock hole.
  • the rotating shaft 424 is inserted into the shaft hole 113, as shown in FIGS. 6 and 7, on the one hand, the rotating shaft 424 can be relative to the shaft hole 113 along the center The line S moves, that is, the landing gear 42 can move along the center line S relative to the mounting plate 11; as shown in FIGS. 8 and 9, on the other hand, the lock pin 425 is not inserted into the When the hole 114 is locked, the rotating shaft 424 can rotate about the center line S relative to the shaft hole 113, that is, the landing gear 42 can rotate about the center line S relative to the mounting plate 11.
  • the locking pin 425 can be aligned with any one of the at least two locking holes 114, so that the locking pin 425 can be inserted into one aligned with it Keyhole 114.
  • the landing gear 42 cannot rotate about the center line S relative to the mounting plate 11, that is, the landing gear 42 is winding
  • the direction of the center line S is fixed relative to the mounting plate 11.
  • the locking pin 425 When the landing gear 42 is folded relative to the fuselage 10, the locking pin 425 is inserted into one of the two locking holes 114, so that the landing gear 42 cannot be wound around the mounting plate 11
  • the center line S rotates, that is, the landing gear 42 is fixed relative to the mounting plate 11 in a direction around the center line S; when the landing gear 42 is deployed relative to the fuselage 10, the lock The pin 425 is inserted into the other of the two lock holes 114, so that the landing gear 42 cannot rotate about the center line S relative to the mounting plate 11, that is, the landing gear 42 is around the center line
  • the direction of S is fixed with respect to the mounting plate 11.
  • the landing gear 42 When the landing gear 42 is unfolded or folded relative to the fuselage 10, the landing gear 42 can move relative to the mounting plate 11 along the center line S, so that the locking pin 425 and the locking hole 114 separate.
  • the pressing structure 43 is used to provide a pressing force for bringing the mounting plate 11 and the landing gear 42 closer to each other along the center line S, so that the first contact surface 112 and the second contact surface 423 Contact.
  • the pressing structure 43 includes a pressing plate 430 and an elastic member 431.
  • the pressing plate 430 is connected to an end of the rotating shaft 424 passing through the shaft hole 113.
  • the pressing plate 430 and the rotating shaft 424 are connected by screws.
  • the elastic member 431 is connected between the pressing plate 430 and the mounting plate 11. When the landing gear 42 moves relative to the mounting plate 11 along the center line S, so that the locking pin 425 is separated from the pin hole 114, the elastic member 431 is compressed to provide the first The contact pressure between the contact surface 112 and the second contact surface 423.
  • the elastic member 431 is a compression spring, which is sleeved on an end of the rotating shaft 424 passing through the shaft hole 113, and the compression spring abuts between the mounting plate 11 and the compression plate 430. According to the actual situation, the compression spring can also be replaced by a shrapnel, an elastic rubber ball, or the like.
  • the elastic member 431 can also be replaced by two magnetic members, for example, magnetic members attracting magnetic attraction are embedded on the two surfaces of the mounting plate 11 and the pressing plate 430 opposite to each other , It is also possible to provide a pressing force that abuts the first contact surface 112 and the second contact surface 423, and the landing gear 42 moves relative to the mounting plate 11 along the center line S so that As the lock pin 425 gradually separates from the lock hole 114, the pressing force gradually increases.
  • the landing gear 42 When the UAV 100 is in use, the landing gear 42 is unfolded or folded relative to the fuselage 10, and when the landing gear 42 needs to switch states, for example, the landing gear 42 is switched from the deployed state To the folded state, you can switch through the following steps:
  • the landing gear 42 moves relative to the mounting plate 11 along the center line S, so that the first contact surface 112 and the second contact surface 423 are away from each other, and at the same time, the lock pin 425 is The keyhole 114 is separated;
  • the landing gear 42 can rotate relative to the mounting plate 11 about the center line S, so that the locking pin 425 is aligned with the at least The corresponding one of the two keyholes 114.
  • the landing gear 42 moves relative to the mounting plate 11 along the center line S, so that the first The contact surface 112 is in contact with the second contact surface 423, and the lock pin 425 is inserted into the lock hole 114 aligned therewith, that is, the landing gear 42 is completely switched from the unfolded state to the folded state.
  • the UAV 100 is configured with a landing gear assembly 40, and the landing gear 42 in the landing gear assembly 40 may be relative to the aircraft
  • the body 10 can be unfolded or folded to achieve the convenience of carrying.
  • the landing gear assembly 40 is a non-electric landing gear assembly, which can be folded or unfolded relative to the fuselage 10 by the user manually driving the landing gear 42 to realize the unmanned aerial vehicle 100 equipped with the landing gear assembly 40
  • the power consumption is small, and because there is no motor, the UAV 100 is light in weight.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
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Abstract

一种无人飞行器（100），包括机身（10）和安装于机身的起落架组件（40），起落架组件包括安装板，起落架（42）和压紧结构（43）。安装板与机身相连，起落架安装于安装板，起落架可相对于安装板绕中心线转动，安装板和起落架中的一个设置有锁孔（114），另一个设置有锁销（425），所述锁孔绕中心线呈圆周分布，压紧结构连接安装板和起落架，用于提供使安装板和起落架沿中心线相互靠近的压紧力。所述无人飞行器配置有起落架组件，并且所述起落架组件中的起落架可相对于所述机身展开或者折叠，可实现所述无人飞行器便于携带。

Description

一种无人飞行器 【技术领域】
本发明涉及飞行器领域，尤其涉及一种无人飞行器。
【背景技术】
起落架作为无人飞行器具有承力兼操纵性的附件装置，在无人飞行器的安全起降过程中担负着极其重要的使命，是无人飞行器的重要部件之一。
目前，起落架一般固定式。
但是，发明人在实现本发明的过程中，发现；采用固定式的起落架不方便携带。因此，现有技术需要改进。
【发明内容】
为了解决上述技术问题，本发明实施例提供一种配置有起落架的无人飞行器，该无人飞行器便于携带。
为了解决上述技术问题，本发明实施例提供以下技术方案：
提供一种无人飞行器，其特征在于，包括机身以及安装于所述机身的起落架组件，所述起落架组件包括：起落架，所述起落架可绕中心线相对于所述机身转动；压紧结构，所述压紧结构一端与所述转轴相连，另一端与所述机身相连，所述压紧结构用于提供使所述起落架沿所述中心线靠近所述机身的压紧力；所述机身和所述起落架两者中的一个设置有锁孔，所述机身和所述起落架两者中的另一个设置有锁销；所述锁销与所述锁孔配合以使得所述起落架相对于所述机身的位置被锁定；所述锁销可与所述锁孔分离，以使得所述起落架可相对于所述机身绕所述中心线转动。
在一些实施例中，所述机身还设有安装板，所述安装板和所述起落架两者中的一个设置有所述锁孔，所述安装板和所述起落架两者中的另一个设置有所述锁销。
在一些实施例中，所述锁销设于所述起落架上，所述锁孔设于所述安装 板上。
在一些实施例中，所述安装板具有第一接触面，所述起落架具有朝向所述第一接触面且与所述第一接触面接触的第二接触面；所述锁销设于所述第一接触面上，且所述锁销沿所述中心线向所述第二接触面延伸，所述锁孔相应地形成于所述第二接触面。
在一些实施例中，所述锁孔设于所述起落架上，所述锁销设于所述安装板上。
在一些实施例中，所述安装板具有第一接触面，所述起落架具有朝向所述第一接触面且与所述第一接触面接触的第二接触面；所述锁销设于所述第二接触面上，且所述锁销沿所述中心线向所述第一接触面延伸，所述锁孔相应地形成于所述第一接触面。
在一些实施例中，所述安装板设置有安装槽，所述第二接触面为所述安装槽的槽底；所述起落架设置有所述第一接触面的一端收容于所述安装槽内。
在一些实施例中，所述起落架与所述机身两者中的一个设置有沿所述中心线设置的转轴，另一个设置有轴孔，所述转轴插入所述轴孔。
在一些实施例中，所述转轴设置在所述起落架上，所述轴孔设置在所述安装板上，且所述轴孔贯穿所述安装板并连通所述机身的内部。
在一些实施例中，所述压紧结构包括压板和弹性件；所述压板设于所述转轴穿过所述轴孔的一端，所述弹性件套设于所述转轴，所述弹性件抵接于所述压板与所述安装板之间。
在一些实施例中，所述弹性件为压簧。
在一些实施例中，所述压板与所述转轴螺纹连接。
与现有技术相比较，在本发明实施例的一种无人飞行器中，所述无人飞行器配置有起落架组件，并且所述起落架组件中的起落架可相对于所述机身展开或者折叠，可实现所述无人飞行器便于携带。
【附图说明】
一个或多个实施例通过与之对应的附图进行示例性说明，这些示例性说明并不构成对实施例的限定，附图中具有相同参考数字标号的元件表示为类似的元件，除非有特别申明，附图中的图不构成比例限制。
图1为本发明其中一实施例提供的一种无人飞行器的立体图；
图2为图1所示的无人飞行器的起落架组件的剖面图，其中起落架组件的起落架被部分省略；
图3为图1所示的无人飞行器的俯视图，其中无人飞行器的部分部件被省略；
图4为图1所示的无人飞行器的主视图，其中两个机翼的长度部分被省略；
图5为图2所示的起落架组件在另一个实施例中的剖面图，其中起落架被部分省略；
图6为图2所示的起落架组件处于第一状态的剖面示意图；
图7为图2所示的起落架组件处于第二状态的剖面示意图；
图8为图2所示的起落架组件处于第三状态的剖面示意图；
图9为图2所示的起落架组件处于第四状态的剖面示意图。
【具体实施方式】
为了便于理解本发明，下面结合附图和具体实施方式，对本发明进行更详细的说明。需要说明的是，当元件被表述“固定于”另一个元件，它可以直接在另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件，它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“垂直的”、“水平的”、“左”、“右”、“内”、“外”以及类似的表述只是为了说明的目的。
除非另有定义，本说明书所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。在本发明的说明书中所使用的术语只是为了描述具体的实施方式的目的，不是用于限制本发明。本说明书所使用的术语“和/或”包括一个或多个相关的所列项目的任意的和所有的组合。
请参阅图1，本发明其中一实施例提供的一种无人飞行器100，可以为多旋翼无人机、固定翼无人机或者倾转旋翼无人机，在本实施例中，以所述无人飞行器100为倾转旋翼无人机为例进行详细说明。
所述无人飞行器100整体为对称结构，具有对称面M，所述无人飞行器 100包括机身10，两个机翼20，两组螺旋桨组件30，以及起落架组件40。其中，所述两个机翼20设置于所述机身10的两相对侧，所述两组螺旋桨组件30分别设置于所述两个机翼20上，所述起落架组件40设置于所述机身10上。
所述机身10大致呈较长的梭形，相对于所述对称面M对称。所述机身10设置有安装板11，所述安装板11可与所述机身10可拆卸地连接，例如，通过螺纹连接件进行连接，所述安装板11也可与所述机身10一体成型。
所述安装板11整体呈平板状，具有安装面110，所述安装面110为所述安装板11背向所述机身10的一面。
所述两个机翼20相对于所述对称面M对称分布。
所述两组螺旋桨组件30相对于所述对称面M对称分布，所述两组螺旋桨组件30可分别相对于所述两个机翼20旋转，例如，所述两组螺旋桨组件30旋转90度，以提供向垂直向上的升力，使得所述无人飞行器100可以垂直升降。
所述起落架组件40的数量为两个，两个所述起落架组件40相对于所述对称面M对称分布。
请一并参阅图2，所述起落架组件40包括起落架42和压紧结构43，所述起落架42安装于所述安装板11，压紧结构43连接所述安装板11和所述起落架42。
可以理解的是，根据实际情况，所述安装板11可以省略，也即所述安装面110直接设置于所述机身10上。
所述安装面110设置有安装槽111，所述安装槽111为圆槽，所述起落架42的一端收容于所述安装槽111，所述安装槽111的槽底设置有第一接触面112，所述轴孔113和所述至少两个锁孔114均设置于所述起落架42，所述轴孔113具有中心线S，所述轴孔连通所述机身10的内部，所述起所述轴孔113和所述至少两个锁孔114均相应地成型与所述第一接触面112，也即所述轴孔113和所述至少两个锁孔114均沿着所述中心线S的方向自所述第一接触面112凹陷形成，所述轴孔113的开口和所述至少两个锁孔114的开口均开设于所述第一接触面上。
请一并参阅图3和图4，所述中心线S与所述对称面M呈第一角度a设置，所述第一角度a为锐角，使得所述起落架42在相对于所述安装板11绕所述中心线S转动时，所述起落架42与所述对称面的开合角c改变，使得所述起落架42可相对于所述机身10展开或者折叠。当所述起落架42相对于所述机身10展开时，所述开合角c为最大值；当所述起落架42相对于所述机身10折叠时，所述开合角c为最小值。
具体地，所述中心线S与所述对称面M之间的所述第一夹角的开口朝向所述机身10的尾部，并且在所述无人飞行器100水平飞行时，所述中心线S水平设置，使得在所述无人飞行器飞行的过程中，所述起落架受到的空气阻力小。
所述至少两个锁孔114均绕所述中心线S呈圆周分布，较优地，所述至少两个锁孔114等距分布。所述至少两个锁孔114中的任意一个可以为通孔，也可以为盲孔，在本实施例中不做限制。
在本实施例中，所述至少两个锁孔114中的任意一个为圆柱状。
在一些其他的实施例中，请参阅图5，所述至少两个锁孔114中的任意一个为半球状。
所述至少两个锁孔114包括第一锁孔和第二锁孔，所述第一锁孔和所述第二锁孔相对于所述中心线S对称设置。
请复参阅图2，所述起落架42包括支撑部420以及延伸于所述支撑部420一端的连接部421。
所述支撑部420为较长的柱状，所述支撑部420用于在所述起落架42相对于所述机身10展开时支撑所述机身10。
所述连接部421为较长的柱状，所述连接部421的轴线与所述中心线S相重合，所述连接部421与所述支撑部420呈第二角度b，所述第二角度b为钝角，使得在所述起落架42相对于所述机身10展开时，所述支撑部420靠近所述连接部421的一端较远离所述连接部421的一端更靠近所述对称面M，即两个所述支撑架42的支撑部420呈八字形，使所述起落架42支撑所述机身10的稳定性得到提升。
进一步地，所述第二角度b大于或者等于所述第一角度a的补角，也即所述第二角度b大于或者等于180度和所述第一角度a两者之差，使得在所述起落架42相对于所述机身10折叠时，所述支撑部420靠近所述连接部421的一端较远离所述连接部421的一端更靠近所述机身10的尾部，使得所述支撑部420相对于所述对称面M平行或者趋于平行。
所述连接部421背离所述支撑部420的一端设置有第二接触面423。
所述第二接触面423朝向所述第一接触面112，在所述第二接触面423上设置有转轴424和锁销425。所述转轴424和所述锁销425均沿所述中心线S向所述第二接触面423延伸。
所述转轴424与所述轴孔113相适配，所述转轴424用于插入所述轴孔113。
可以理解的是，根据实际情况，所述转轴424和所述轴孔113的位置可以互换，即所述转轴424设置于所述第一接触面112，所述轴孔113设置于所述第二接触面423，只要所述第一接触面112和所述第二接触面423两者中的一个设置有所述轴孔113，另一个设置有所述转轴424即可。
所述锁销425与所述至少两个锁孔114中的任意一个相适配，所述锁销425用于插入所述至少两个锁孔113中的任意一个。
可以理解的是，根据实际情况，所述锁销425和所述至少两个锁孔114的位置可以互换，即所述锁销425设置于所述第一接触面112，所述至少两个锁孔114设置于所述第二接触面423，只要所述第一接触面112和所述第二接触面123两者中的一个设置有所述锁销425，另一个设置有所述至少两个锁孔114即可。
所述锁销425包括第一锁销和第二锁销，所述第一锁销用于插入所述第一锁孔和所述第二锁孔中的一个，所述第二锁销用于插入所述第一锁孔和所述第二锁孔中的另一个。当所述第一锁销插入所述第一锁孔时，所述第二锁销插入所述第二锁孔；当所述第二锁销插入所述第二锁孔时，所述第二锁销插入所述第一锁孔。
请一并参阅图6至图9，所述转轴424插入所述轴孔113，如图6和图7所示，一方面使得所述转轴424可相对于所述轴孔113沿着所述中心线S移 动，即所述起落架42可相对于所述安装板11沿着所述中心线S移动；如图8和图9所示，另一方面使得在所述锁销425没有插入所述锁孔114时，所述转轴424可相对于所述轴孔113绕着所述中心线S转动，即所述起落架42可相对于所述安装板11绕着所述中心线S转动。
当所述起落架42相对于所述安装板11转动时，所述锁销425可对准所述至少两个锁孔114中的任意一个，使得所述锁销425可插入一个与其对准的锁孔114。
当所述锁销425插入所述至少两个锁孔114中的任意一个时，所述起落架42不能相对于所述安装板11绕所述中心线S转动，即所述起落架42在绕所述中心线S的方向上相对于所述安装板11固定。通过在所述起落架42与所述安装板11之间设置锁销425与所述锁孔114，可使得在所述起落架42相对于所述机身10展开或者折叠时，所述起落架42不会转动，提高了所述起落架42支撑所述机身10的稳定性。
当所述起落架42相对于所述机身10折叠时，所述锁销425插入所述两个锁孔114中的一个，使得所述起落架42不能相对于所述安装板11绕所述中心线S转动，即所述起落架42在绕着所述中心线S的方向上相对于所述安装板11固定；当所述起落架42相对于所述机身10展开时，所述锁销425插入所述两个锁孔114中的另一个，使得所述起落架42不能相对于所述安装板11绕所述中心线S转动，即所述起落架42在绕着所述中心线S的方向上相对于所述安装板11固定。
当所述起落架42相对于所述机身10展开或者折叠时，所述起落架42可相对于所述安装板11沿所述中心线S移动，使得所述锁销425与所述锁孔114分离。
所述压紧结构43用于提供使所述安装板11和所述起落架42沿所述中心线S相互靠近的压紧力，使得所述第一接触面112和所述第二接触面423相抵接。
所述压紧结构43包括压板430和弹性件431。其中，所述压板430连接于所述转轴424穿过所述轴孔113的一端，较优地，所述压板430和所述转 轴424通过螺纹连接。所述弹性件431连接于所述压板430与所述安装板11之间。当所述起落架42相对于所述安装板11沿所述中心线S移动，使得所述锁销425与所述销孔114分离时，所述弹性件431压缩，以提供将所述第一接触面112和所述第二接触面423相抵接的压紧力。
所述弹性件431为压簧，其套设于所述转轴424穿过所述轴孔113的一端，并且所述压簧抵接于所述安装板11与所述压板430之间。根据实际情况，所述压簧还可替代为弹片、弹性橡胶球等。
需要说明的是，根据实际情况，所述弹性件431还可以替换为两个磁性件，例如，在所述安装板11和所述压板430彼此相对的两面上分别嵌设磁性相吸的磁性件，也能够提供将所述第一接触面112和所述第二接触面423相抵接的压紧力，且在所述起落架42相对于所述安装板11沿所述中心线S移动，使得所述锁销425逐渐与所述锁孔114分离的过程中，所述压紧力逐渐增大。
所述无人飞行器100在使用时，所述起落架42相对于所述机身10展开或者折叠，当所述起落架42需要切换状态时，例如，所述起落架42从所述展开状态切换至折叠状态，可通过以下步骤进行切换：
首先，所述起落架42相对于所述安装板11沿所述中心线S移动，使所述第一接触面112与所述第二接触面423相互远离，同时，所述锁销425与所述锁孔114相分离；
然后，在所述锁销424与所述锁孔114相分离后，所述起落架42可相对于所述安装板11绕所述中心线S转动，使所述锁销425对准所述至少两个锁孔114中的相应的一个。
最后，在所述锁销425对准所述至少两个锁孔114中的相应的一个后，所述起落架42相对于所述安装板11沿所述中心线S移动，使所述第一接触面112与所述第二接触面423接触，所述锁销425插入与其对准的锁孔114，即所述起落架42完成从展开状态切换至折叠状态。
与现有技术相比较，本发明实施例提供的无人飞行器100中，所述无人飞行器100配置有起落架组件40，并且所述起落架组件40中的起落架42可 相对于所述机身10展开或者折叠，可实现所述便于携带。
另外所述起落架组件40为非电动起落架组件，可通过用户手动驱动所述起落架42相对于所述机身10折叠或者展开，可实现配置有所述起落架组件40的无人飞行器100耗电量小，由于没有电机，所述无人飞行器100重量较轻。
最后应说明的是：以上实施例仅用以说明本发明的技术方案，而非对其限制；在本发明的思路下，以上实施例或者不同实施例中的技术特征之间也可以进行组合，步骤可以以任意顺序实现，并存在如上所述的本发明的不同方面的许多其它变化，为了简明，它们没有在细节中提供；尽管参照前述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 (12)

  1. 一种无人飞行器(100)，其特征在于，包括机身(10)以及安装于所述机身(10)的起落架组件(40)，所述起落架组件(40)包括：
    起落架(42)，所述起落架(42)可绕中心线(S)相对于所述机身(10)转动；
    压紧结构(43)，所述压紧结构(43)一端与所述转轴(424)相连，另一端与所述机身(10)相连，所述压紧结构(43)用于提供使所述起落架(42)沿所述中心线(S)靠近所述机身(10)的压紧力；
    所述机身(10)和所述起落架(42)两者中的一个设置有锁孔(114)，所述机身(10)和所述起落架(42)两者中的另一个设置有锁销(425)；
    所述锁销(425)与所述锁孔(114)配合以使得所述起落架(42)相对于所述机身(10)的位置被锁定；
    所述锁销(425)可与所述锁孔(114)分离，以使得所述起落架(42)可相对于所述机身(10)绕所述中心线(S)转动。
  2. 根据权利要求1所述的无人飞行器(100)，其特征在于，所述机身(10)还设有安装板(11)，所述安装板(11)和所述起落架(42)两者中的一个设置有所述锁孔(114)，所述安装板(11)和所述起落架(42)两者中的另一个设置有所述锁销(425)。
  3. 根据权利要求2所述的无人飞行器(100)，其特征在于，所述锁销(425)设于所述起落架(42)上，所述锁孔(114)设于所述安装板(11)上。
  4. 根据权利要求3所述的无人飞行器(100)，其特征在于，所述安装板(11)具有第一接触面(112)，所述起落架(42)具有朝向所述第一接触面(112)且与所述第一接触面(112)接触的第二接触面(423)；
    所述锁销(425)设于所述第一接触面(112)上，且所述锁销(425)沿所述中心线(S)向所述第二接触面(423)延伸，所述锁孔(114)相应地形成于所述第二接触面(423)。
  5. 根据权利要求2所述的无人飞行器(100)，其特征在于，所述锁孔(114)设于所述起落架(42)上，所述锁销(425)设于所述安装板(11)上。
  6. 根据权利要求5所述的无人飞行器(100)，其特征在于，所述安装板 (11)具有第一接触面(112)，所述起落架(42)具有朝向所述第一接触面(112)且与所述第一接触面(112)接触的第二接触面(423)；
    所述锁销(425)设于所述第二接触面(423)上，且所述锁销(425)沿所述中心线(S)向所述第一接触面(112)延伸，所述锁孔(114)相应地形成于所述第一接触面(112)。
  7. 根据权利要求2-6中任一项所述的无人飞行器(100)，其特征在于，所述安装板(11)设置有安装槽(111)，所述第二接触面(112)为所述安装槽(111)的槽底；
    所述起落架(42)设置有所述第一接触面(112)的一端收容于所述安装槽(111)内。
  8. 根据权利要求1-7中任一项所述的无人飞行器(100)，其特征在于，所述起落架(42)与所述机身(10)两者中的一个设置有沿所述中心线(S)设置的转轴(424)，另一个设置有轴孔(113)，所述转轴(424)插入所述轴孔(113)。
  9. 根据权利要求8所述的无人飞行器(100)，其特征在于，所述转轴(424)设置在所述起落架(42)上，所述轴孔(113)设置在所述安装板(11)上，且所述轴孔(113)贯穿所述安装板(11)并连通所述机身(10)的内部。
  10. 根据权利要求9所述的无人飞行器，其特征在于，所述压紧结构(43)包括压板(430)和弹性件(431)；
    所述压板(430)设于所述转轴(424)穿过所述轴孔(113)的一端，所述弹性件(431)套设于所述转轴(424)，所述弹性件(431)抵接于所述压板(430)与所述安装板(11)之间。
  11. 根据权利要求10所述的无人飞行器(100)，其特征在于，所述弹性件(431)为压簧。
  12. 根据权利要求10或11所述的无人飞行器(100)，其特征在于，所述压板(430)与所述转轴(424)螺纹连接。
PCT/CN2019/128059 2018-12-24 2019-12-24 一种无人飞行器 Ceased WO2020135448A1 (zh)

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