WO2017118082A1 - 减震结构、云台及飞行器 - Google Patents

减震结构、云台及飞行器 Download PDF

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Publication number
WO2017118082A1
WO2017118082A1 PCT/CN2016/098881 CN2016098881W WO2017118082A1 WO 2017118082 A1 WO2017118082 A1 WO 2017118082A1 CN 2016098881 W CN2016098881 W CN 2016098881W WO 2017118082 A1 WO2017118082 A1 WO 2017118082A1
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WO
WIPO (PCT)
Prior art keywords
shock absorbing
absorbing structure
structure according
hole
hanging plate
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PCT/CN2016/098881
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English (en)
French (fr)
Inventor
张永生
王佳迪
陈星元
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深圳市大疆创新科技有限公司
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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
Publication of WO2017118082A1 publication Critical patent/WO2017118082A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/04—Aircraft characterised by the type or position of power plants of piston type
    • B64D27/08—Aircraft characterised by the type or position of power plants of piston type within, or attached to, fuselages

Definitions

  • the invention relates to a shock absorbing structure, a platform and an aircraft having the shock absorbing structure.
  • the rubber shock absorption has a good shock absorption effect on the medium and low frequency vibrations.
  • the rubber shock absorption has a weak damping effect on the high frequency vibration, and the rubber shock absorption is weak.
  • the optional parameters on the damping coefficient are relatively simple, which makes the rubber shock absorption unable to adapt to the condition changes under different vibration environments.
  • Most of the aircraft need to be loaded with loads of different weights. The rubber shock absorption can not meet the shock absorption requirements when the aircraft is loaded with many different loads.
  • a shock absorbing structure includes a deformable shock absorbing member.
  • the damper member is provided with a receiving cavity, and the accommodating cavity is filled with a damping absorbing material, and the damper member and the damping damper material can be combined and damped.
  • the two ends of the shock absorbing member are respectively connected to the two connected components.
  • the damper member includes a damper portion, and the accommodating cavity is formed in the damper portion.
  • the sidewall of the damper portion includes a curved structure.
  • the shock absorbing structure includes a first hanging plate, and the damping member is connected to one of the two connected components through the first hanging plate.
  • the shock absorbing structure further includes a second hanging plate spaced apart from the first hanging plate, the damping member is connected between the first hanging plate and the second hanging plate, and passes through the second hanging plate Connected to the other of the two connected components.
  • the shock absorbing member includes a first connecting portion, and the first hanging plate is connected to the first connecting portion.
  • the first hanging plate is provided with a first connecting hole;
  • the first connecting portion includes a first stop And a first supporting portion connected to the first stopping portion, the first supporting portion is received in the first connecting hole, and the first stopping portion bears on the first hanging plate.
  • the size of the first stopping portion is larger than the size of the end of the first supporting portion and the first stopping portion.
  • the damper member includes a second connecting portion opposite to the first connecting portion, and the second hanging plate is connected to the second connecting portion.
  • the second hanging plate is provided with a second connecting hole;
  • the second connecting portion includes a second stopping portion and a second supporting portion connected to the second stopping portion, wherein the second supporting portion is received in the second supporting portion
  • the second connecting portion is connected to the second hanging plate in the two connecting holes.
  • the size of the second stopping portion is larger than the size of the end of the second supporting portion and the second stopping portion.
  • the damper member is provided with a first through hole and/or a second through hole communicating with the receiving cavity, and the first through hole and/or the second through hole can be replaced and filled in the receiving cavity The damping shock absorbing material.
  • damper portion of the damper member is connected to the first connecting portion and the second connecting portion, and the first through hole is opened in the first connecting portion; the second connecting hole is formed in the second connecting portion.
  • a central axis of the first connecting hole, a central axis of the second connecting hole, a central axis of the first through hole, and a central axis of the second through hole substantially coincide.
  • the shock absorbing member is a rubber shock absorbing member.
  • the filling in the receiving cavity of the damping member is foam.
  • a pan/tilt head includes a first connecting member, a second connecting member and a shock absorbing structure as described above, the shock absorbing structure being coupled to the first connecting member and the second connecting member.
  • An aircraft includes a fuselage and a pan/tilt as described above, the pan/tilt being coupled to the fuselage.
  • An aircraft includes a fuselage and a shock absorbing structure as described above, the shock absorbing structure being coupled to the fuselage.
  • the damping damping material forms a composite shock absorption with the damping portion, and the damping member can be adapted to different by simply replacing the damping material. Shock absorption requirements under weight load conditions.
  • FIG. 1 is a schematic view showing a partial use state of an aircraft according to a preferred embodiment of the present invention.
  • FIG. 2 is a schematic perspective view of the shock absorbing structure of FIG. 1.
  • FIG. 3 is a schematic plan view showing the structure of the shock absorbing structure of FIG. 2.
  • Figure 4 is a cross-sectional view of the shock absorbing structure of Figure 3 taken along the line IV-IV.
  • Shock absorption structure 100 First hanging board 10 First connection hole 11 Second hanging board 20 Second connection hole twenty one Shock absorber 30 First connection 31 First stop 311 First support 312 First through hole 313 Second connection 32 Second stop 321 Second support 322 Second through hole 323 Damping unit 33 Containment chamber 331 Shock absorbing material 34 PTZ bracket 40 Yuntai 200 First connector 201 Second connector 202 Third connector 203 Fourth connector 204 Aircraft 300
  • a component when referred to as being “fixed” to another component, it can be directly on the other component or the component can be present.
  • a component When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • a component When a component is considered to be “set to” another component, it can be placed directly on another component or possibly with a centered component.
  • the terms “vertical,” “horizontal,” “left,” “right,” and the like, as used herein, are for illustrative purposes only.
  • an aircraft 300 such as an unmanned aerial vehicle or the like, includes a body 301 and a platform 200 connected to the body 301.
  • the platform 200 includes a shock absorbing structure. 100 and PTZ bracket 40.
  • the aircraft 300 is used to carry a load 400 through which the load 400 is coupled to the fuselage 301.
  • the shock absorbing structure 100 is capable of absorbing vibrations from the fuselage 301 and/or from the external environment that the load 400 is subjected to.
  • the load 400 is coupled to the shock absorbing structure 100 through the pan/tilt bracket 40. It can be appreciated that in other embodiments, the load 400 can be directly coupled to the shock absorbing structure 100.
  • the load 400 is an imaging element such as a camera, a video camera or the like.
  • the pan/tilt bracket 40 can be a single-axis, dual-axis or multi-axis bracket.
  • the platform 200 includes a first connecting member 201, a second connecting member 202 spaced apart from the first connecting member 201, a third connecting member 203 connecting the second connecting member 202 and the body 301, and a connection The fourth connector 204 of the body 301.
  • the shock absorbing structure 100 connects the first connecting member 201 and the second connecting member 202.
  • the first connector 201 carries a load 400.
  • the first connecting member 201 and the second connecting member 202 are both plate-shaped structures
  • the third connecting member 203 is a plate member hinged to the body 301
  • the fourth connecting member 204 is disposed on the body.
  • first connecting member 201 is connected to the third connecting member 203 by a connecting rod, and the second connecting member 202 is erected on the fourth connecting member 204.
  • the first connecting member 201 and the second connecting member 202 are respectively connected to upper and lower ends of the shock absorbing structure 100.
  • the number of the third connecting members 203 is two, and the two connecting members 203 are oppositely disposed.
  • first connecting member 201 and the second connecting member 202 can also be other structures such as a frame, and the third connecting member 203 can be fixed to the body 301 or movably connected to the machine.
  • Other structures of body 301 such as rods, blocks, frames, and the like.
  • the number, structure, and connection manner of the first connecting member 201, the second connecting member 202, the third connecting member 203, and the fourth connecting member 204 can be changed according to actual needs.
  • the shock absorbing structure 100 includes a first hanging plate 10 , a second hanging plate 20 spaced apart from the first hanging plate 10 , and a damping member 30 connecting the first hanging plate 10 and the second hanging plate 20 .
  • the first hanging plate 10 is connected to the first connecting member 201.
  • the first hanging plate 10 is provided with a first connecting hole 11
  • the first hanging plate 10 is sleeved on the damping member 30 through the first connecting hole 11 .
  • the second hanging plate 20 is connected to the second connecting member 202.
  • the second hanging plate 20 is provided with a second connecting hole 21 , and the second hanging plate 20 is sleeved on the damping member 30 through the second connecting hole 21 .
  • the two ends of the shock absorbing member 30 can be connected to the first connecting member 201 and the second connecting member 202 by other means.
  • the two ends of the damper member 30 can be directly fixed to the two connected components of the first connecting member 201 and the second connecting member 202, or one end is directly fixed to the first connecting member 201 or the first
  • the two connectors 202 are connected to the second connector 202 or the first connector 201 by a hanging plate.
  • the structures of the first hanging plate 10 and the second hanging plate 20 are also changed to other structures such as a fixing frame and a hook.
  • the shock absorbing member 30 is located between the first hanging plate 10 and the second hanging plate 20.
  • the damper member 30 has a hollow shape, and the damper member 30 includes a first connecting portion 31, a second connecting portion 32 opposite to the first connecting portion 31, and the first connecting portion 31 and the second connecting portion. Damping portion 33 of 32.
  • the first company The connecting portion 31 includes a first stopping portion 311 and a first supporting portion 312 connected to the first stopping portion 311. The first supporting portion 312 is received in the first connecting hole 11 to make the shock absorbing member 30 The first connecting portion 31 is connected to the first hanging plate 10.
  • the first supporting portion 312 extends from the first stopping portion 311 toward a surface of the damper portion 33 away from the first stopping portion 311, and the first stopping portion 311 bears against the first hanging portion 311 On the board 10.
  • the first stopping portion 311 is connected to the end of the first supporting portion 312.
  • the size of the first stopping portion 311 is larger than the size of the end of the first supporting portion 312 and the first stopping portion 311.
  • the first supporting portion 312 is prevented from being detached from the first connecting hole 11 , thereby preventing the shock absorbing member 30 from being disconnected from the first hanging plate 10 .
  • the first connecting portion 31 is further provided with a first through hole 313 , and the first through hole 313 extends through the first connecting portion 31 .
  • the first through hole 313 is a circular hole. It can be understood that in other embodiments, the first through hole 313 can be any other suitable shape, such as a square hole, an elliptical hole or the like.
  • the second connecting portion 32 is connected to the second hanging plate 20 .
  • the second connecting portion 32 includes a second stopping portion 321 and a second supporting portion 322 connected to the second stopping portion 321 .
  • the second supporting portion 322 is received in the second connecting hole 21 to make the second
  • the connecting portion 32 is connected to the second hanging plate 20.
  • the second stopping portion 321 is connected to the end of the second supporting portion 322.
  • the size of the second stopping portion 321 is larger than the size of the end of the second supporting portion 322 and the second stopping portion 321
  • the second connecting portion 32 is prevented from being disconnected from the second hanging plate 20.
  • the second connecting portion 32 defines a second through hole 323 , and the second through hole 323 extends through the second connecting portion 32 .
  • the second through hole 323 is a stepped hole.
  • the stepped diameter of the second through hole 323 is less than or equal to the diameter of the first through hole 313 to prevent the damping damper material 34 filled in the damper portion 33 from being detached from the second
  • first connecting portion 31 and the second connecting portion 32 can also be omitted, and the two ends of the damper portion 33 are respectively fixed to the two elements connected.
  • first through hole 313 and the second through hole 323 can be formed in other portions of the damper member 30, such as the side portions of the first connecting portion 31 and the second connecting portion 32.
  • the shock absorbing portion 33 is up and the like.
  • the central axis of the first connection hole 11 , the central axis of the second connection hole 21 , the central axis of the first through hole 313 , and the central axis of the second through hole 323 substantially coincide.
  • the damper portion 33 defines a receiving cavity 331 that communicates with the first through hole 313 and the second through hole 323.
  • the receiving cavity 331 is configured to receive the damper damping material 34.
  • the damping damping material 34 received in the receiving cavity 331 can be replaced by the first through hole 313 and the second through hole 323.
  • the damping coefficient damping damping material allows the damping member 30 to adapt to different damping requirements.
  • the side wall of the damper portion 33 includes a curved surface structure. In the present embodiment, the inner and outer surfaces of the side wall of the damper portion 33 are curved.
  • the two side faces of the side wall of the damper portion 33 may also have a curved surface on one side and a flat surface on the other side; or both surfaces have a curved surface.
  • the curved surface may be a curved surface, a wavy surface or the like. It can be understood that the side wall of the damper portion 33 may be flat on both sides, and the damper portion 33 may be a columnar shape, a rectangular parallelepiped shape, a truncated cone shape or the like.
  • the damper portion 33 is a spherical body made of rubber; it can be understood that in other embodiments, the damper portion 33 can be made of other elastic materials, such as silica gel, etc.; 34 is a foam. It can be understood that in other embodiments, the damping material 34 can be cotton, foam, composite pearl cotton, sponge, cotton, or the like. The damper portion 33 and the damper damper material 34 form a composite damper by the cooperation of the rubber and the foam.
  • the first hanging plate 10 is connected to the first connecting portion 31 of the damper member 30
  • the second hanging plate 20 is connected to the second connecting portion 32 of the damper member 30
  • the damping material 34 is filled in the receiving cavity 331 of the damper portion 33 through the first through hole 313 and the second through hole 323.
  • the first hanging plate 10 of the shock absorbing structure 100 is connected to the first connecting member 201 of the platform 200, and the second hanging plate 20 is connected to the second connecting member 202.
  • the second connecting member 202 of the platform 200 is connected to the body 301 of the aircraft 300 through the connecting member 203.
  • the number of the shock absorbing structures 100 of the pan/tilt head 200 is four, and the four shock absorbing structures 100 are spaced apart. It can be understood that in other embodiments, the number of the shock absorbing structures 100 can be according to actual needs. Increase or decrease.
  • the first hanging plate 10 and the second hanging plate 20 may be omitted, and the damping member 30 is directly disposed between the first connecting member 201 and the second connecting member 202.
  • the damping member 30 is damped by the load 400 mounted on the first connecting member 201 of the pan/tilt 200 by internal compression; it can be understood that in other embodiments, the damper member 30 can be shock-absorbing by being stretched.
  • the application of the shock absorbing structure 100 is not limited to the pan/tilt head.
  • the shock absorbing structure 100 can also be used for other structures having shock absorbing requirements, such as motors, landing gears, and the like that require isolation vibration.
  • the damping damping material forms a composite shock absorption with the damping portion, and the damping member can be made by simply replacing the damping material.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Dampers (AREA)

Abstract

一种减震结构（100），云台（200）及飞行器（300），减震结构（100）包括可变形的减震件（30），减震件（30）开设有收容腔（331），收容腔（331）内填充有阻尼减震材料（34），减震件（30）与阻尼减震材料（34）能够进行复合式减震。

Description

减震结构、云台及飞行器 技术领域
本发明涉及一种减震结构、具有该减震结构的云台及飞行器。
背景技术
现有的飞行器大都采用单纯的橡胶减震方案，橡胶减震对中低频的震动具有较好的减震效果，然而，橡胶减震对高频的震动的减震效果较弱，且橡胶减震由于结构及加工工艺的限制其在阻尼系数上可选的参数比较单一，导致橡胶减震无法适应不同振动环境下的条件变化。飞行器大都需要挂载多种不同重量的负载，橡胶减震无法满足飞行器挂载多种不同负载时的减震需求。
发明内容
有鉴于此，有必要提供一种能够满足不同减震需求的减震结构、云台及飞行器。
一种减震结构，其包括可变形的减震件。该减震件开设有收容腔，该收容腔内填充有阻尼减震材料，该减震件与该阻尼减震材料能够进行复合式减震。
进一步的，该减震件的两端分别与被连接的两个元件连接。
进一步的，该减震件包括减震部，该收容腔开设于该减震部。
进一步的，该减震部的侧壁包括曲面结构。
进一步的，该减震结构包括第一挂板，该减震件通过该第一挂板与该被连接的两个元件的其中一个连接。
进一步的，该减震结构还包括与该第一挂板间隔设置的第二挂板，该减震件连接于该第一挂板及该第二挂板之间，并通过该第二挂板与该被连接的两个元件中的另一个连接。
进一步的，该减震件包括第一连接部，该第一挂板与该第一连接部相连接。
进一步的，该第一挂板开设有第一连接孔；该第一连接部包括第一止挡 部及连接于该第一止挡部的第一支撑部，该第一支撑部收容在该第一连接孔内，该第一止挡部承靠在该第一挂板上。
进一步的，该第一止挡部的尺寸大于该第一支撑部与该第一止挡部相连接的末端的尺寸。
进一步的，该减震件包括与该第一连接部相背的第二连接部，该第二挂板与该第二连接部相连接。
进一步的，该第二挂板开设有第二连接孔；该第二连接部包括第二止挡部及连接于该第二止挡部的第二支撑部，该第二支撑部收容在该第二连接孔内，使该第二连接部与该第二挂板相连接。
进一步的，该第二止挡部的尺寸大于该第二支撑部与该第二止挡部相连接的末端的尺寸。
进一步的，该减震件开设有与该收容腔相连通的第一通孔及/或第二通孔，通过该第一通孔及/或该第二通孔能够更换填充在该收容腔内的该阻尼减震材料。
进一步的，该减震件的减震部连接该第一连接部及该第二连接部，该第一通孔开设于该第一连接部；该第二连接孔开设于该第二连接部。
进一步的，该第一连接孔的中心轴、该第二连接孔的中心轴、该第一通孔的中心轴及该第二通孔的中心轴大致重合。
进一步的，该减震件为橡胶减震件。
进一步的，该减震件的收容腔内的填充物为泡棉。
一种云台，其包括第一连接件、第二连接件及如上所述的减震结构，该减震结构与该第一连接件及该第二连接件连接。
一种飞行器，其包括机身及如上所述的云台，该云台连接于该机身。
一种飞行器，其包括机身及如上所述的减震结构，该减震结构连接于该机身。
采用本发明提供的减震结构、云台及飞行器，该阻尼减震材料与该减震部形成复合式减震，通过简单的更换该阻尼减震材料，即可使得该减震件可以适应不同重量负载情况下的减震需求。
附图说明
图1是本发明较佳实施方式提供的飞行器的局部使用状态示意图。
图2是图1中的减震结构的立体结构示意图。
图3是图2中的减震结构的平面结构示意图。
图4是图3中的减震结构沿IV-IV方向的剖视图。
主要元件符号说明
减震结构 100
第一挂板 10
第一连接孔 11
第二挂板 20
第二连接孔 21
减震件 30
第一连接部 31
第一止挡部 311
第一支撑部 312
第一通孔 313
第二连接部 32
第二止挡部 321
第二支撑部 322
第二通孔 323
减震部 33
收容腔 331
减震材料 34
云台支架 40
云台 200
第一连接件 201
第二连接件 202
第三连接件 203
第四连接件 204
飞行器 300
机身 301
负载 400
如下具体实施方式将结合上述附图进一步说明本发明。
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。
需要说明的是，当组件被称为“固定于”另一个组件，它可以直接在另一个组件上或者也可以存在居中的组件。当一个组件被认为是“连接”另一个组件，它可以是直接连接到另一个组件或者可能同时存在居中组件。当一个组件被认为是“设置于”另一个组件，它可以是直接设置在另一个组件上或者可能同时存在居中组件。本文所使用的术语“垂直的”、“水平的”、“左”、“右”以及类似的表述只是为了说明的目的。
除非另有定义，本文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。本文中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例的目的，不是旨在于限制本发明。本文所使用的术语“及/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。
下面结合附图，对本发明的一些实施方式作详细说明。在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
请参阅图1至图4，本发明较佳实施方式提供的飞行器300，如无人飞行器等，其包括机身301及连接于该机身301的云台200，该云台200包括减震结构100及云台支架40。该飞行器300用于搭载负载400，该负载400通过该云台200连接于该机身301。该减震结构100能够缓冲该负载400受到的来自该机身301及/或来自外部环境的振动。本实施方式中，该负载400通过云台支架40连接于该减震结构100。可以理解，在其他实施方式中，该负载400可以直接与该减震结构100连接。本实施方式中，该负载400为拍摄元件，例如相机、摄像机等。该云台支架40可为单轴、双轴或多轴支架。
该云台200包括第一连接件201、与该第一连接件201相隔一定距离的第二连接件202、连接该第二连接件202和该机身301的第三连接件203，以及连接于该机身301的第四连接件204。该减震结构100连接该第一连接件201及该第二连接件202。该第一连接件201搭载负载400。本实施例中，该第一连接件201和该第二连接件202均为板状结构，该第三连接件203为铰接于机身301的板材，该第四连接件204为设置于机身301底部的碳管。具体地，该第一连接件201通过连杆连接于该第三连接件203，该第二连接件202搭设于该第四连接件204上。该第一连接件201和该第二连接件202分别与该减震结构100的上下两端连接。该第三连接件203的数量为两个，两个该第三连接件203相对设置。
可以理解，在其他实施方式中，该第一连接件201和该第二连接件202也可为框架等其他结构，该第三连接件203可为固定于该机身301或活动连接于该机身301的其他结构，如杆状、块状、框架等。该第一连接件201、该第二连接件202、该第三连接件203及该第四连接件204的数量、结构以及和该机身301的连接方式均可以根据实际需要改变。
该减震结构100包括第一挂板10、与该第一挂板10间隔设置的第二挂板20及连接该第一挂板10和该第二挂板20的减震件30。该第一挂板10连接于第一连接件201。本实施方式中，该第一挂板10开设有第一连接孔11，该第一挂板10通过该第一连接孔11套设在该减震件30上。该第二挂板20连接于该第二连接件202。本实施方式中，该第二挂板20开设有第二连接孔21，该第二挂板20通过该第二连接孔21套设在该减震件30上。可以理解，该减震件30两端可通过其他方式连接到该第一连接件201和该第二连接件202上。如，该减震件30的两端可直接固定到该第一连接件201和该第二连接件202的两个被连接的元件上，或一端直接固定于该第一连接件201或该第二连接件202，另一端通过挂板连接到该第二连接件202或该第一连接件201。且该第一挂板10和该第二挂板20的结构也可变更为如固定架、卡勾等其他结构。
该减震件30位于该第一挂板10与该第二挂板20之间。该减震件30呈中空状，该减震件30包括第一连接部31、与该第一连接部31相背的第二连接部32及连接该第一连接部31和该第二连接部32的减震部33。该第一连 接部31包括第一止挡部311及连接于该第一止挡部311的第一支撑部312，该第一支撑部312收容在该第一连接孔11内，使该减震件30的第一连接部31与该第一挂板10相连接。该第一支撑部312自该第一止挡部311朝向该减震部33的一表面向远离该第一止挡部311的方向延伸，该第一止挡部311承靠在该第一挂板10上。该第一止挡部311连接于该第一支撑部312的末端，该第一止挡部311的尺寸大于该第一支撑部312与该第一止挡部311相连接的末端的尺寸，以防止该第一支撑部312自该第一连接孔11脱离，进而防止该减震件30与该第一挂板10脱离连接。
该第一连接部31还开设有第一通孔313，该第一通孔313贯穿该第一连接部31。本实施方式中，该第一通孔313为圆孔；可以理解，在其他实施方式中，该第一通孔313可以为其他任意合适形状的孔，如方孔、椭圆形孔等。
该第二连接部32连接于该第二挂板20。该第二连接部32包括第二止挡部321及连接于该第二止挡部321的第二支撑部322，该第二支撑部322收容在该第二连接孔21内，使该第二连接部32与该第二挂板20相连接。该第二止挡部321连接于该第二支撑部322的末端，该第二止挡部321的尺寸大于该第二支撑部322与该第二止挡部321相连接的末端的尺寸，以防止该第二连接部32与该第二挂板20脱离连接。该第二连接部32开设有第二通孔323，该第二通孔323贯穿该第二连接部32。本实施方式中，该第二通孔323为阶梯孔。该第二通孔323的阶梯直径小于等于该第一通孔313的直径，以防止填充在该减震部33内的阻尼减震材料34在重力作用下从该第二通孔323脱离该减震部33。
可以理解，该第一连接部31和该第二连接部32也可省略，而将该减震部33的两端分别固定到被连接的两个元件上。
可以理解，该第一通孔313及该第二通孔323可以开设于该减震件30的其他部位，如可以开设于该第一连接部31及该第二连接部32的侧部、该减震部33上等。本实施方式中，该第一连接孔11的中心轴、该第二连接孔21的中心轴、该第一通孔313的中心轴及该第二通孔323的中心轴大致重合。
该减震部33开设有与该第一通孔313及该第二通孔323相连通的收容腔331，该收容腔331用于收容该阻尼减震材料34。收容在该收容腔331内的阻尼减震材料34能够通过第一通孔313及该第二通孔323被更换为不同 阻尼系数的阻尼减震材料，使该减震件30适应不同的减震需求。该减震部33的侧壁包括曲面结构，在本实施方式中，该减震部33的侧壁的内外面均呈弧面。该减震部33的侧壁的两个侧面也可一个面呈曲面，另一个面呈平面；或两个面均呈曲面。该曲面可为弧面、波浪形表面等结构。可以理解，该减震部33的侧壁也可为两个面均呈平面，且该减震部33可为圆柱状、长方体状、锥台状等。
本实施方式中，该减震部33是由橡胶制成的球状体；可以理解，在其他实施方式中，该减震部33可以由其他弹性材料制成，如硅胶等；该阻尼减震材料34为泡棉，可以理解，在其他实施方式中，该阻尼减震材料34可以为棉花、泡沫塑料、复合型珍珠棉、海绵、棉花等。该减震部33与该阻尼减震材料34通过橡胶与泡棉的配合形成复合式减震。
该第一挂板10连接于该减震件30的第一连接部31，该第二挂板20连接于该减震件30的第二连接部32。该阻尼减震材料34通过该第一通孔313及该第二通孔323填充在该减震部33的收容腔331内。
该减震结构100的第一挂板10连接于该云台200的第一连接件201，该第二挂板20连接于该第二连接件202。该云台200的第二连接件202通过该连接件203连接于该飞行器300的机身301。本实施方式中，该云台200的减震结构100的数量为四个，四个该减震结构100间隔设置；可以理解，在其他实施方式中，该减震结构100的数量可以根据实际需要增加或者减少。
可以理解，在其他实施方式中，可以省略该第一挂板10及该第二挂板20，该减震件30直接设置在该第一连接件201与该第二连接件202之间。当该减震件30两端直接固定到该第一连接件201和该第二连接件202时，在该第一连接件201上开设通孔，以便更换该减震件30的收容腔331内的该阻尼减震材料34。本实施方式中，该减震件30通过内压缩的方式为搭载于该云台200的第一连接件201上的该负载400进行减震；可以理解，在其他实施方式中，该减震件30可以通过被拉伸的方式进行减震。
该减震结构100的应用并不限于云台，该减震结构100还可以用于其他有减震需求的结构，如电机、起落架等需要隔离振动的结构上。
采用本发明提供的减震结构、云台及飞行器，该阻尼减震材料与该减震部形成复合式减震，通过简单的更换该阻尼减震材料，即可使得该减震件可 以适应不同重量负载情况下的减震需求。
以上实施方式仅用以说明本发明的技术方案而非限制，尽管参照以上较佳实施方式对本发明进行了详细说明，本领域的普通技术人员应当理解，可以对本发明的技术方案进行修改或等同替换都不应脱离本发明技术方案的精神和范围。

Claims (20)

  1. 一种减震结构，其包括可变形的减震件，其特征在于：该减震件开设有收容腔，该收容腔内填充有阻尼减震材料，该减震件与该阻尼减震材料能够进行复合式减震。
  2. 如权利要求1所述的减震结构，其特征在于：该减震件的两端分别与被连接的两个元件连接。
  3. 如权利要求2所述的减震结构，其特征在于：该减震件包括减震部，该收容腔开设于该减震部。
  4. 如权利要求3所述的减震结构，其特征在于：该减震部的侧壁包括曲面结构。
  5. 如权利要求3所述的减震结构，其特征在于：该减震结构包括第一挂板，该减震件通过该第一挂板与该被连接的两个元件的其中一个连接。
  6. 如权利要求5所述的减震结构，其特征在于：该减震结构还包括与该第一挂板间隔设置的第二挂板，该减震件连接于该第一挂板及该第二挂板之间，并通过该第二挂板与该被连接的两个元件中的另一个连接。
  7. 如权利要求6所述的减震结构，其特征在于：该减震件包括第一连接部，该第一挂板与该第一连接部相连接。
  8. 如权利要求7所述的减震结构，其特征在于：该第一挂板开设有第一连接孔；该第一连接部包括第一止挡部及连接于该第一止挡部的第一支撑部，该第一支撑部收容在该第一连接孔内，该第一止挡部承靠在该第一挂板上。
  9. 如权利要求8所述的减震结构，其特征在于：该第一止挡部的尺寸大于该第一支撑部与该第一止挡部相连接的末端的尺寸。
  10. 如权利要求7所述的减震结构，其特征在于：该减震件包括与该第一连接部相背的第二连接部，该第二挂板与该第二连接部相连接。
  11. 如权利要求10所述的减震结构，其特征在于：该第二挂板开设有第二连接孔；该第二连接部包括第二止挡部及连接于该第二止挡部的第二支撑部，该第二支撑部收容在该第二连接孔内，使该第二连接部与该第二挂板相连接。
  12. 如权利要求11所述的减震结构，其特征在于：该第二止挡部的尺寸大于该第二支撑部与该第二止挡部相连接的末端的尺寸。
  13. 如权利要求3所述的减震结构，其特征在于：该减震件开设有与该收容腔相连通的第一通孔及/或第二通孔，通过该第一通孔及/或该第二通孔能够更换填充在该收容腔内的该阻尼减震材料。
  14. 如权利要求11或13所述的减震结构，其特征在于：该减震件的减震部连接该第一连接部及该第二连接部，该第一通孔开设于该第一连接部；该第二连接孔开设于该第二连接部。
  15. 如权利要求8、11或13所述的减震结构，其特征在于：该第一连接孔的中心轴、该第二连接孔的中心轴、该第一通孔的中心轴及该第二通孔的中心轴大致重合。
  16. 如权利要求1所述的减震结构，其特征在于：该减震件为橡胶减震件。
  17. 如权利要求1所述的减震结构，其特征在于：该减震件的收容腔内的填充物为泡棉。
  18. 一种云台，其包括第一连接件、第二连接件及如权利要求1-17任一项所述的减震结构，该减震结构与该第一连接件及该第二连接件连接。
  19. 一种飞行器，其包括机身及如权利要求18所述的云台，该云台连接于该机身。
  20. 一种飞行器，其包括机身及如权利要求1-17任一项所述的减震结构，该减震结构连接于该机身。
PCT/CN2016/098881 2016-01-05 2016-09-13 减震结构、云台及飞行器 WO2017118082A1 (zh)

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