WO2019037035A1 - 飞行器减震结构 - Google Patents

飞行器减震结构 Download PDF

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Publication number
WO2019037035A1
WO2019037035A1 PCT/CN2017/098845 CN2017098845W WO2019037035A1 WO 2019037035 A1 WO2019037035 A1 WO 2019037035A1 CN 2017098845 W CN2017098845 W CN 2017098845W WO 2019037035 A1 WO2019037035 A1 WO 2019037035A1
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WIPO (PCT)
Prior art keywords
shock absorbing
absorbing structure
intermediate bracket
structure according
aircraft
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PCT/CN2017/098845
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English (en)
French (fr)
Inventor
田瑜
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田瑜
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Application filed by 田瑜 filed Critical 田瑜
Priority to PCT/CN2017/098845 priority Critical patent/WO2019037035A1/zh
Publication of WO2019037035A1 publication Critical patent/WO2019037035A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B64U50/14—Propulsion using external fans or propellers ducted or shrouded
    • 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
    • B64U30/26—Ducted or shrouded rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
    • 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
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body

Definitions

  • the invention relates to an aircraft damping structure, in particular to an unmanned aerial vehicle damping structure.
  • the technical problem solved by the present invention is to provide an aircraft shock absorbing structure in order to overcome the vibration of the fixed platform on the aircraft of the prior art.
  • An aircraft shock absorbing structure characterized in that it comprises an intermediate bracket, an outer frame and a damper element, the damper elements being respectively connected to the intermediate bracket and the outer frame, and the damper element
  • the intermediate bracket is spaced from the outer frame.
  • the vibration is separated by the damping element between the intermediate bracket and the outer frame, thereby greatly reducing the vibration interference received by the external frame.
  • the external frame minimizes the damage of the aircraft to the human body without increasing the weight of the structure, and can be easily connected by hand, which greatly shortens the distance from the user, makes the user experience better, and can provide closer graphics and movies.
  • the damping elements are respectively engaged with the intermediate bracket and the outer frame.
  • the intermediate bracket is fixed with a rotor.
  • the rotor includes a motor fixed to the intermediate bracket and a blade fixed to the motor.
  • the outer frame comprises an outer facing, and the damping element is coupled to the outer facing.
  • the number of the outer protective faces is two, and the two outer protective faces are respectively located at two sides of the intermediate bracket.
  • the outer frame comprises a surrounding outer edge, and the outer outer surfaces are respectively connected to the two sides of the surrounding outer edge.
  • the outer facing is parallel to the intermediate bracket.
  • the damper element comprises a neck portion, a compression portion and a fixed end, wherein the neck portion is coupled to the intermediate bracket, the fixed end is coupled to the outer frame, and the compression portion is located at the Between the neck and the fixed end, and the compression portion is used to generate deformation.
  • the deformation of the compression portion can greatly absorb the vibration.
  • the damping element is made of an elastic material.
  • the shock absorbing element is flexible and can be easily compressed to be snapped into the intermediate bracket and the outer frame for fixing. It is also very convenient when disassembling.
  • the intermediate bracket is provided with a limiting portion, and the neck portion is connected to the limiting portion.
  • the outer facing surface is provided with a limiting hole, and the fixed end is connected to the limiting hole.
  • the fixed end includes a fixed body extending along an axial direction of the damper member, and an outer edge extending along a radial direction of the damper member, wherein the limiting hole is sleeved in the The fixing body is fixed, and the limiting hole is limited between the outer end edge and the compression portion.
  • the pan/tilt is fixed on the outer frame.
  • the positive progress of the present invention is that, by the use of the present invention, the vibration is isolated by the damper element between the intermediate bracket and the outer frame, thereby greatly reducing the vibration interference received by the outer frame.
  • the external frame minimizes the damage of the aircraft to the human body without increasing the weight of the structure, and can be easily connected by hand, which greatly shortens the distance from the user, makes the user experience better, and can provide closer graphics and movies.
  • FIG. 1 is a schematic perspective view showing the structure of an aircraft shock absorbing structure according to a preferred embodiment of the present invention.
  • FIG. 2 is a schematic top plan view of a shock absorber structure of an aircraft according to a preferred embodiment of the present invention.
  • FIG 3 is a side view showing the structure of an aircraft shock absorbing structure according to a preferred embodiment of the present invention.
  • FIG. 4 is a schematic perspective view of a middle bracket of a preferred embodiment of the present invention.
  • FIG. 5 is a schematic top plan view of an intermediate bracket according to a preferred embodiment of the present invention.
  • FIG. 6 is a schematic top plan view of an outer frame according to a preferred embodiment of the present invention.
  • Figure 7 is a schematic perspective view of the outer frame of the preferred embodiment of the present invention.
  • Figure 8 is a schematic view showing the connection of a damper element in accordance with a preferred embodiment of the present invention.
  • Figure 9 is a schematic view showing the structure of a damper element according to a preferred embodiment of the present invention.
  • this embodiment discloses an aircraft shock absorbing structure.
  • the aircraft shock absorbing structure of the present embodiment includes an intermediate bracket 2, an outer frame 1, and a damper member 7.
  • 1 to 9 are vertical propulsion rotors 3 and first horizontal rotors 41; second horizontal rotors 42, pan/tilt 5, and antennas 6 are used to explain the operating environment of the aircraft damping structure, and are not the structure of the aircraft damping structure itself.
  • the vertical propulsion rotor 3 and the first horizontal rotor 41 are removed; the second horizontal rotor 42, the pan/tilt 5, and the antenna 6 do not affect the normal operation of the aircraft damping structure of the embodiment.
  • the port 115; the opening 116; the quadrangular frame 21; the mounting frame 211; and the extension frame 22 are all disposed in a further preferred embodiment of the aircraft damping structure, and do not affect the normal operation of the aircraft damping structure of the embodiment.
  • the intermediate bracket 1 is provided with four vertical propulsion rotors 3, a first horizontal rotor 41 and a second horizontal rotor 42.
  • the intermediate bracket 2 includes a quadrangular frame 21, and two extension brackets 22 connected to adjacent sides of the quadrilateral frame 21, and the first horizontal rotor 41 and the second horizontal rotor 42 are respectively fixed to two. On the extension frame 22.
  • the four corners of the quadrilateral frame 21 are provided with a mounting bracket 211, and the vertical propulsion rotor 3 is fixed to the mounting bracket 211.
  • the vertical propulsion rotor 3, a first horizontal rotor 41 and a second horizontal rotor 42 in this embodiment may each be provided to include a motor and blades attached to the motor.
  • the vertical propulsion rotor 3 includes a vane 31 and a motor 32. It is fixed to the mounting bracket 211 by the motor 32.
  • the outer frame 1 includes an outer face 12 and an outer face 13.
  • the number of outer protective faces is set to two.
  • an outer facing may also be employed, as well as other functions of the invention.
  • the outer cover 12 and the outer cover 13 are respectively located on both sides of the intermediate bracket 2. And the outer cover 12 and the outer cover 13 are parallel to the intermediate bracket 2.
  • the outer frame 1 includes a peripheral edge 11 which is attached to both sides of the outer edge 11, respectively.
  • the surrounding outer edge includes a first side edge 111, a second side edge 112, a third side edge 113, and a fourth side edge 114.
  • first side edge 111 is opposite the first horizontal propulsion rotor 41
  • second side edge 112 is opposite to the second horizontal propulsion rotor 42.
  • the first side edge 111 is provided with an opening 115
  • the second side 112 is provided with an opening 116.
  • the opening 115 and the opening 116 minimize the resistance of the first horizontal propulsion rotor 41 and the second horizontal propulsion rotor 42 to improve propulsion efficiency.
  • a pan/tilt 5 is fixed on the third side edge 113, and the fourth side edge 114 is fixed on the sky.
  • Line 6 Further, as shown in FIGS. 1 and 6, a control frame 14 is provided at the center of the outer face 12.
  • a protective layer may be disposed around the outer edge 11. In the event that the aircraft hits a wall or a branch, it will not cause damage to the aircraft's body and propulsion rotor due to the protective layer surrounding the outer edge 11. Do not crash after collision does not affect the effect of use.
  • the material of the protective layer is preferably a PU or a sponge material.
  • a mesh structure is provided on the outer cover 12 and the outer cover 13.
  • the mesh structure has a minimum area in the plan view direction, thereby improving lift efficiency.
  • the damper members 7 are respectively coupled to the intermediate bracket 2 and the outer frame 1, and the damper member 7 separates the intermediate bracket 2 from the outer frame 1.
  • the damper elements 7 of the present embodiment are respectively engaged with the intermediate bracket 2 and the outer frame 1.
  • the damping element 7 includes a neck portion 72, a compression portion 73, and a fixed end 71.
  • the neck 72 is connected to the intermediate bracket 2. As shown in FIG. 4 and FIG. 8 , the intermediate bracket 2 is provided with a limiting portion 212 , and the neck portion 72 is engaged with the limiting portion 212 .
  • the fixed end 71 is coupled to the outer face 12 and the outer face 13 of the outer frame 1.
  • the fixed end 71 includes a fixed body 712 extending along the axial direction of the damper element 7, and an outer end edge 711 extending along the radial direction of the damper element 7,
  • the outer facing surface 12 is provided with a limiting hole 121
  • the outer protective surface 13 is also provided with a limiting hole (not shown).
  • the fixed end 71 is connected to the limiting hole 121.
  • the limiting hole 121 is sleeved on the fixing body 712 , and the limiting hole 121 is limited between the outer edge 711 and the compression portion 73 .
  • the compression portion 73 is located between the neck portion 72 and the fixed end 71, and the compression portion 73 is used to generate deformation.
  • the deformation of the compression portion 73 can greatly absorb the vibration.
  • the damping element 7 can be made of an elastic material.
  • the damper element 7 has elasticity and can be easily compressed to be snapped into the intermediate bracket 2 and the outer frame 1 for fixing. It is also very convenient when disassembling.
  • the damper element 7 is coupled to the outer guard surface 12 and the outer guard surface 13, a large amount of vibration generated by the vertical propulsion rotor 3, the first horizontal rotor 41 and the second horizontal rotor 42 is filtered by the damper element 7 during flight. Therefore, the vibration of the outer frame 1 is greatly reduced.
  • the outer frame 1 also minimizes the damage of the aircraft to the human body without increasing the weight of the structure, and can be easily connected by hand, which greatly shortens the distance from the user, makes the user experience better, and can provide closer graphics and film.
  • the positive progress of the present invention is that, by the use of the present invention, the vibration is isolated by the damper element between the intermediate bracket and the outer frame, thereby greatly reducing the vibration interference received by the outer frame.
  • the external frame minimizes the damage of the aircraft to the human body without increasing the weight of the structure, and can be easily connected by hand, which greatly shortens the distance from the user, makes the user experience better, and can provide closer graphics and movies.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Vibration Prevention Devices (AREA)

Abstract

一种飞行器减震结构，其包括中间支架（2）、外部框架（1）以及减震元件（7），所述减震元件（7）分别与所述中间支架（2）和所述外部框架（1）连接，并且所述减震元件（7）将所述中间支架（2）和所述外部框架（1）隔开。中间支架（2）和外部框架（1）之间通过减震元件（7）隔离了震动，从而大幅减少外部框架（1）受到的震动干扰。外部框架（1）在不增加结构重量的情况下让飞行器对人体的伤害降到最低，可以从容的手接，大大缩短了与用户间的距离，让用户体验更好，能提供更接近的图形和影片。

Description

飞行器减震结构 技术领域
本发明涉及一种飞行器减震结构，特别是一种无人飞行器减震结构。
背景技术
现有的无人飞行器通常采用倾斜移动的方式进行移动。在移动时，整个飞行器的螺旋桨产生了大量震动，导致飞行器上固定的云台也产生了震动，导致产生图像大量抖动。因此，云台上的摄像设备必须通过光学防抖等手段防止图形不稳定。但这些手段都不能得到令人满意的稳定图像。
发明内容
本发明解决的技术问题是为了克服现有技术飞行器上固定的云台容易产生震动，提供一种飞行器减震结构。
本发明是通过下述技术方案来解决上述技术问题：
一种飞行器减震结构，其特点在于，其包括中间支架、外部框架以及减震元件，所述减震元件分别与所述中间支架和所述外部框架连接，并且所述减震元件将所述中间支架和所述外部框架隔开。
其中，中间支架和外部框架之间通过减震元件隔离了震动，从而大幅减少外部框架收到的震动干扰。外部框架在不增加结构重量的情况下让飞行器对人体的伤害降到最低，可以从容的手接，大大缩短了与用户间的距离，让用户体验更好，能提供更接近的图形和影片。
较佳地，所述减震元件分别卡接于所述中间支架和所述外部框架。
较佳地，所述中间支架上固定有旋翼。
较佳地，所述旋翼包括固定在所述中间支架上的电机，以及与所述电机固定的叶片。
较佳地，所述外部框架包括外护面，所述减震元件与所述外护面连接。
较佳地，所述外护面的数量为两个，两个所述外护面分别位于所述中间支架的两侧。
较佳地，所述外部框架包括环绕外缘，两个所述外护面分别连接于所述环绕外缘两侧。
较佳地，所述外护面与所述中间支架平行。
较佳地，所述减震元件包括颈部、压缩部和固定端，其中，所述颈部连接于所述中间支架，所述固定端连接于所述外部框架，所述压缩部位于所述颈部和所述固定端之间，且所述压缩部用于产生形变。压缩部产生形变后可以大幅吸收震动。
较佳地，所述减震元件由弹性材料制成。减震元件具有弹性，可以方便的压缩从而卡进中间支架和外部框架进行固定。在拆卸时也非常便捷。
较佳地，所述中间支架上设置有限位部，所述颈部连接于所述限位部。
较佳地，所述外护面上设置有限位孔，所述固定端连接于所述限位孔。
较佳地，所述固定端包括沿所述减震元件的轴向延伸的固定本体，以及沿所述减震元件的径向延伸的外端缘，其中，所述限位孔套设于所述固定本体，且所述限位孔被限位于所述外端缘与所述压缩部之间。
较佳地，所述外部框架上固定有云台。
本发明中，上述优选条件在符合本领域常识的基础上可任意组合，即得本发明的各较佳实施例。
本发明的积极进步效果在于：通过本发明的运用，中间支架和外部框架之间通过减震元件隔离了震动，从而大幅减少外部框架收到的震动干扰。外部框架在不增加结构重量的情况下让飞行器对人体的伤害降到最低，可以从容的手接，大大缩短了与用户间的距离，让用户体验更好，能提供更接近的图形和影片。
附图说明
图1为本发明较佳实施例的飞行器减震结构立体结构示意图。
图2为本发明较佳实施例的飞行器减震结构俯视结构示意图。
图3为本发明较佳实施例的飞行器减震结构侧视结构示意图。
图4为本发明较佳实施例的中间支架立体结构示意图。
图5为本发明较佳实施例的中间支架俯视结构示意图。
图6为本发明较佳实施例的外部框架俯视结构示意图。
图7为本发明较佳实施例的外部框架立体结构示意图。
图8为本发明较佳实施例的减震元件连接示意图。
图9为本发明较佳实施例的减震元件结构示意图。
附图标记说明：
外部框架1；环绕外缘11；第一侧缘111；第二侧缘112；第三侧缘113；第四侧缘114；开口115；开口116；外护面12；限位孔121；外护面13；控制价14；中间支架2；四边形框21；安装架211；限位部212；延伸架22；垂直推进旋翼3；叶片31；电机32；第一水平旋翼41；第二水平旋翼42；云台5、天线6、减震元件7；固定端71；外端缘711；固定本体712；颈部72；压缩部73。
具体实施方式
如图1-9所示，本实施例公开了一种飞行器减震结构。如图1、图2和图4所示，本实施例的飞行器减震结构包括中间支架2、外部框架1以及减震元件7。其中，图1-图9垂直推进旋翼3、第一水平旋翼41；第二水平旋翼42、云台5、天线6均为了解释飞行器减震结构的运用环境，并非飞行器减震结构的本身结构，去除垂直推进旋翼3、第一水平旋翼41；第二水平旋翼42、云台5、天线6均不会影响到本实施例的飞行器减震结构的正常工作。
其中，第一侧缘111；第二侧缘112；第三侧缘113；第四侧缘114；开 口115；开口116；四边形框21；安装架211；延伸架22均为飞行器减震结构进一步较佳实施例的设置，均不会影响到本实施例的飞行器减震结构的正常工作。
如图4所示，中间支架1上设置有四个垂直推进旋翼3、第一水平旋翼41和一第二水平旋翼42。
如图4和图5所示，中间支架2包括四边形框21，以及连接在四边形框21的相邻两边的两个延伸架22，第一水平旋翼41和第二水平旋翼42分别固定在两个延伸架22上。
其中，为了将垂直推进旋翼3固定在四边形框21上，四边形框21的四个角上设置有安装架211，垂直推进旋翼3固定在安装架211上。
本实施例中的垂直推进旋翼3、一第一水平旋翼41和一第二水平旋翼42均可以设置为包括电机和连接在所述电机上的叶片。如图4所示，垂直推进旋翼3包括了叶片31和电机32。通过电机32固定在安装架211上。
如图6和图7所示，外部框架1包括外护面12和外护面13。本实施例中将外护面的数量设置为两个。但是在其他实施例中也可以采用一个外护面，也能够实现本发明的其他功能。
如图1和图7所示，本实施例中外护面12和外护面13分别位于中间支架2的两侧。且外护面12和外护面13与中间支架2平行。外部框架1包括环绕外缘11，外护面12和外护面13分别连接于环绕外缘11的两侧。
进一步地，如图7所示，环绕外缘包括第一侧缘111、第二侧缘112、第三侧缘113和第四侧缘114。其中，如图2所示，第一侧缘111与第一水平推进旋翼41相对，第二侧缘112与第二水平推进旋翼42相对。
如图1和图3所示，第一侧缘111上设置有开口115，第二侧,112上设置有开口116。开口115和开口116最大限度减少了第一水平推进旋翼41和第二水平推进旋翼42的阻力，提高了推进效率。
如图2所示，第三侧缘113上固定有云台5，第四侧缘114上固定有天 线6。此外，如图1和图6所示，外护面12的中部设置有控制架14。
环绕外缘11上可以设置保护层。在万一飞行器撞到墙面或者树枝时，由于环绕外缘11的保护层设置，不会造成对飞行器的机体和推进旋翼的损坏。起到碰撞后不坠毁不影响使用的效果。保护层的材料优选为PU或者海绵材料。
外护面12和外护面13上设置有网状结构。网状结构在俯视方向拥有最小面积，从而提高升力效率。
如图8所示，本实施例中，减震元件7分别与中间支架2和外部框架1连接，并且减震元件7将中间支架2和外部框架1隔开。
如图7和图8所示，本实施例的减震元件7分别卡接于中间支架2和所述外部框架1。其中，减震元件7包括颈部72、压缩部73和固定端71。
其中，颈部72连接于中间支架2。如图4和图8所示，中间支架2上设置有限位部212，颈部72卡接于限位部212。
如图7和图8所示，固定端71连接于外部框架1的外护面12和外护面13。其中，固定端71包括沿减震元件7的轴向延伸的固定本体712，以及沿减震元件7的径向延伸的外端缘711，
如图7和图8所示外护面12上设置有限位孔121，外护面13也设置有限位孔(图中未标注)。固定端71连接于限位孔121中。其中，限位孔121套设于固定本体712，且限位孔121被限位于外端缘711与压缩部73之间。
如图7和图8所示，压缩部73位于颈部72和固定端71之间，且压缩部73用于产生形变。压缩部73产生形变后可以大幅吸收震动。
减震元件7可以由弹性材料制成。减震元件7具有弹性，可以方便的压缩从而卡进中间支架2和外部框架1进行固定。在拆卸时也非常便捷。
由于减震元件7与外护面12和外护面13连接，因此，飞行时，垂直推进旋翼3、第一水平旋翼41和第二水平旋翼42产生的大量震动均被减震元件7滤除，从而极大幅度减少了外部框架1的震动。
外部框架1在不增加结构重量的情况下还让飞行器对人体的伤害降到最低，可以从容的手接，大大缩短了与用户间的距离，让用户体验更好，能提供更接近的图形和影片。
本发明的积极进步效果在于：通过本发明的运用，中间支架和外部框架之间通过减震元件隔离了震动，从而大幅减少外部框架收到的震动干扰。外部框架在不增加结构重量的情况下让飞行器对人体的伤害降到最低，可以从容的手接，大大缩短了与用户间的距离，让用户体验更好，能提供更接近的图形和影片。
虽然以上描述了本发明的具体实施方式，但是本领域的技术人员应当理解，这些仅是举例说明，在不背离本发明的原理和实质的前提下，可以对这些实施方式做出多种变更或修改。因此，本发明的保护范围由所附权利要求书限定。

Claims (14)

  1. 一种飞行器减震结构，其特征在于，其包括中间支架、外部框架以及减震元件，所述减震元件分别与所述中间支架和所述外部框架连接，并且所述减震元件将所述中间支架和所述外部框架隔开。
  2. 如权利要求1所述的飞行器减震结构，其特征在于，所述减震元件分别卡接于所述中间支架和所述外部框架。
  3. 如权利要求1所述的飞行器减震结构，其特征在于，所述中间支架上固定有旋翼。
  4. 如权利要求3所述的飞行器减震结构，其特征在于，所述旋翼包括固定在所述中间支架上的电机，以及与所述电机固定的叶片。
  5. 如权利要求1-4中至少一项所述的飞行器减震结构，其特征在于，所述外部框架包括外护面，所述减震元件与所述外护面连接。
  6. 如权利要求5所述的飞行器减震结构，其特征在于，所述外护面的数量为两个，两个所述外护面分别位于所述中间支架的两侧。
  7. 如权利要求6所述的飞行器减震结构，其特征在于，所述外部框架包括环绕外缘，两个所述外护面分别连接于所述环绕外缘两侧。
  8. 如权利要求5所述的飞行器减震结构，其特征在于，所述外护面与所述中间支架平行。
  9. 如权利要求1-8中至少一项所述的飞行器减震结构，其特征在于，所述减震元件包括颈部、压缩部和固定端，其中，所述颈部连接于所述中间支架，所述固定端连接于所述外部框架，所述压缩部位于所述颈部和所述固定端之间，且所述压缩部用于产生形变。
  10. 如权利要求1-8中至少一项所述的飞行器减震结构，其特征在于，所述减震元件由弹性材料制成。
  11. 如权利要求9所述的飞行器减震结构，其特征在于，所述中间支架 上设置有限位部，所述颈部连接于所述限位部。
  12. 如权利要求9所述的飞行器减震结构，其特征在于，所述外护面上设置有限位孔，所述固定端连接于所述限位孔。
  13. 如权利要求12所述的飞行器减震结构，其特征在于，所述固定端包括沿所述减震元件的轴向延伸的固定本体，以及沿所述减震元件的径向延伸的外端缘，其中，所述限位孔套设于所述固定本体，且所述限位孔被限位于所述外端缘与所述压缩部之间。
  14. 如权利要求1-13中至少一项所述的飞行器减震结构，其特征在于，所述外部框架上固定有云台。
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CN104379959A (zh) * 2014-03-31 2015-02-25 深圳市大疆创新科技有限公司 减震装置和应用所述减震装置的飞行器
CN205440860U (zh) * 2015-12-22 2016-08-10 优利科技有限公司 飞行器
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KR20120102880A (ko) * 2011-03-09 2012-09-19 유세혁 옥터콥터 장치 및 이의 제어 방법
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