WO2015149263A1 - 减震装置和应用所述减震装置的飞行器 - Google Patents

减震装置和应用所述减震装置的飞行器 Download PDF

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Publication number
WO2015149263A1
WO2015149263A1 PCT/CN2014/074499 CN2014074499W WO2015149263A1 WO 2015149263 A1 WO2015149263 A1 WO 2015149263A1 CN 2014074499 W CN2014074499 W CN 2014074499W WO 2015149263 A1 WO2015149263 A1 WO 2015149263A1
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WO
WIPO (PCT)
Prior art keywords
base
damper
extension
abutting
damper device
Prior art date
Application number
PCT/CN2014/074499
Other languages
English (en)
French (fr)
Inventor
林�源
赵涛
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.)
Filing date
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 PCT/CN2014/074499 priority Critical patent/WO2015149263A1/zh
Priority to CN201480001516.6A priority patent/CN104379959B/zh
Publication of WO2015149263A1 publication Critical patent/WO2015149263A1/zh

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Classifications

    • 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
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
    • F16F7/104—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted
    • F16F7/108—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted on plastics springs
    • 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
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/08—Arrangements of cameras
    • 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
    • F16F15/08—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 with rubber springs ; with springs made of rubber and metal

Definitions

  • the invention belongs to the technical field of aircrafts, and in particular to a damping device and an aircraft using the same.
  • a related art aircraft generally carries a load to perform a certain function, for example, when the load is a camera or a camera, it can be mounted on the aircraft to achieve aerial photography.
  • the aircraft includes a fuselage and a power unit coupled to the fuselage to provide flight power to the aircraft.
  • the load is coupled to the fuselage.
  • the load and the body are directly connected to such a hard connection.
  • the vibration generated when the power unit on the airframe operates is directly transmitted to the load, causing the load to vibrate along with the body, so that the aircraft cannot meet the needs of practical applications.
  • a damper device comprising a base and a mount spaced apart from the base, wherein the damper device further comprises at least one of the base and the a damper member between the mounts and a detachment preventing member respectively connecting the base and the mount, one end of the damper member is connected to the base, and the other end of the damper member and the mount Connected, the anti-drop member penetrates at least partially through the shock absorbing member.
  • the anti-drop member includes a first 4 joint for connecting with the base 4, and a second distance from the first joint for a distance from the first joint.
  • the connecting portion and the supporting portion connecting the first abutting portion and the second abutting portion and penetrating the damping member.
  • the second extension has a tapered shape.
  • the first junction is movably abutted from the outer surface of the mount away from the mount.
  • the support portion includes a first extension portion connected to the second abutment portion, a second extension portion extending away from the first abutment portion from the first extension portion, and from the first a second extension portion extending away from the first extension portion; a projection of the second extension portion along an extension direction of the support portion falls within the third extension portion; the second extension portion A projection along a direction away from the support portion also falls within the first extension.
  • the first extension of the support portion is provided with a continuation portion connected to the second abutment portion and a locking portion respectively connecting the continuation portion and the second extension portion;
  • a projection that faces away from the extending direction of the support portion falls within the locking portion;
  • a projection of the continuation portion along a direction in which the support portion extends also falls within the locking portion.
  • the shock absorbing member is made of an elastic material.
  • the damper portion is provided in a spherical shape.
  • the present invention further provides a damper device including a base and a mounting seat spaced apart from the base, wherein the damper device further includes at least one shock absorbing member and a fall prevention member, the shock absorbing member One end is connected to the base, and the other end of the shock absorbing member is connected to the mounting seat, and the anti-drop member has flexibility and is directly wound around the base and the mounting seat.
  • the invention further provides an aircraft comprising a damping device as described above.
  • the aircraft includes a body and a stabilizing device mounted on the body, the body is connected to the base of the damper device, and the stabilizing device and the damper device are The mounts are connected.
  • the damper device of the present invention has the damper member added between the base and the mount, so that it has a shock absorbing function. Further, the present invention further provides an aircraft to which the damper device is applied, which damper device can suppress or reduce the vibration generated by the aircraft.
  • Figure 1 is a perspective view of a damper device of the present invention.
  • FIG. 2 is an exploded perspective view of the damper device of the present invention.
  • Fig. 3 is a perspective view of a damper portion of the damper device of the present invention.
  • FIG. 4 is a perspective view of a first embodiment of an anti-drop member of a damper device to which the present invention is applied. Exploded map.
  • Fig. 5 is a perspective exploded view showing a second embodiment of the anti-drop member of the damper device to which the present invention is applied.
  • Fig. 6 is a perspective assembled view of a second embodiment of the anti-drop member of the damper device to which the present invention is applied.
  • Fig. 7 is a perspective exploded view showing a third embodiment of the anti-drop member of the damper device to which the present invention is applied.
  • Figure 8 is a perspective view of an aircraft to which the damper device of the present invention is applied.
  • Figure 9 is an enlarged view of a portion A in Figure 8.
  • a damper device 10 reduces unnecessary vibrations by a load (not shown) mounted thereon, and includes a base 1 and a certain distance from the base 1 .
  • the mount 2 of the distance is at least one shock absorbing member 3 connected to both the base 1 and the mount 2.
  • the base 1 includes a bottom plate 11 , a thousand bottom arms 12 scattered from the bottom plate 11 , and a first receiving groove 13 extending through the bottom arm 12 .
  • the mounting base 2 includes a mounting plate 21, a plurality of mounting arms 22 scattered from the mounting plate 21, and a second receiving slot (not labeled) extending through the mounting arm 22.
  • the bottom arm 12 and the mounting arm 22 are each provided with four and cross-shaped. Therefore, the number of the bottom arm 12, the first receiving slot 13, the mounting arm 22, and the second receiving slot is four, and the bottom arm 12 and the mounting arm 22 are matched.
  • the shock absorbing member 3 is also provided with four. One end of any of the damper members 3 is connected to the bottom arm 12 of the base 1, and correspondingly, the other end is connected to the mounting arm 22 of the mount 2.
  • the damper member 3 is hollow and is interposed between the base 1 and the mounting base 2, and includes a first connecting portion 31 received in the first receiving slot 13 of the base 1. And a second connecting portion 32 housed in the second receiving groove of the mounting seat 2 and a damping portion 33 connecting the first connecting portion 31 and the second connecting portion 32.
  • the shock absorbing member 3 is made of an elastic material such as rubber, silicone, sponge or spring.
  • the damper portion 33 is provided in a spherical shape. In operation, the mounting seat 2 reduces the unnecessary vibration generated by the base 1 for the load lapped on the mounting seat 2 in a manner of stretching the shock absorbing member 3.
  • the first connecting portion 31 and the second connecting portion 32 are respectively movably received in the first receiving groove 13 and the second receiving groove.
  • the shock absorbing member 3 is easily detached from between the mount 2 and/or the base 1.
  • the damper device 10 is further provided with four anti-drop members 4 for preventing the damper member 3 from falling off from the base 1 and/or the mount 2.
  • the anti-drop member 4 includes a first 4 joint portion 41 for contacting the base 14 and a second distance from the mounting seat 24 at a distance from the first 4 joint portion 41.
  • the fourth connecting portion 42 connects the first and second abutting portions 41 and the second abutting portion 42 and penetrates the supporting portion 43 of the damper member 3.
  • the support portion 43 sequentially penetrates the first receiving groove 13 of the base 1 , the first connecting portion 31 of the damper 3 , the damper portion 33 , and the damper 3
  • the second connecting portion 32 and the second receiving groove of the mounting seat 2 .
  • the first abutting portion 41 is configured to abut the outer surface of the base 1 away from the mounting seat 2; the second abutting portion 42 is configured to abut the mounting base 2 away from the base 1 The outer surface.
  • the support portion 43 of the anti-drop member 4 completely penetrates the damper member 3.
  • the anti-drop member 4 can partially penetrate the damper member 3, for example, the detachment preventing member 4 only penetrates the damper portion 33.
  • the second junction portion 42 is provided integrally with the support portion 43.
  • the first joint portion 41 may be fixedly coupled to the support portion 43 by threading or riveting or the like to facilitate assembly and disassembly of the shock absorbing device 10.
  • the first abutting portion 41 includes the first abutting plate 411 for abutting against the base 1 and a fixing portion extending from the first abutting plate 411 to the mounting seat 2
  • the support portion 43 is inserted into the fixing hole 413 through the fixing hole 413 which penetrates the first 4th plate 411 and the fixing portion 412 at the same time.
  • the support portion 43 is provided with an external thread 430 away from one end of the second abutting portion 42, and an internal thread is disposed in the fixing hole 413.
  • the support portion 43 is coupled to the first splicing portion 41 by an external thread 430 and an internal thread of the fixing hole 413.
  • the fixing portion 412 can be omitted, and the fixing hole 413 is directly connected to the first tab 411.
  • first connecting portion 41, the second connecting portion 42 and the supporting portion 43 are separately provided, and when assembled, the first abutting portion 41 and the first portion Two abutment
  • the portion 42 is fixedly coupled to the support portion 43 by techniques well known in the art, such as by threads or riveting.
  • the anti-drop member 40 of the second embodiment is substantially similar to the anti-drop member 4 of the first embodiment, except that:
  • the support portion 403 includes a first extension portion 431 connected to the second junction portion 402, a second extension portion 432 extending from the first extension portion 431 away from the second abutment portion 402, and The third extension portion 432 extends from the second extension portion 432 away from the first extension portion 431.
  • the second extension portion 432 is located between the first extension portion 431 and the third extension portion 433.
  • a projection of the second extension portion 432 along the extending direction of the support portion 403 falls within the third extension portion 433; a projection of the second extension portion 432 along a direction extending away from the support portion 403 falls within the Inside the first extension portion 431.
  • the first abutting portion 401 is sleeved on the second extending portion 432 through the fixing hole 4013 and is locked between the first extending portion 431 and the third extending portion 433, so that the first A 4 joint portion 401 is not easily detached from the support portion 403.
  • the second extending portion 432 has a tapered shape, and the cross section of the second extending portion 432 is reduced from the first extending portion 431 toward the third extending portion 433.
  • the third extending portion 433 is also tapered, in a direction from the first extending portion 431 to the third extending portion 433, the third extending portion for facilitating assembly of the first 4th connecting portion 401. The section of the portion 433 is reduced.
  • the anti-drop member 400 of the third embodiment is substantially similar to the anti-drop member 40 of the second embodiment, and the difference is:
  • the first joint portion 4001 is sleeved on the second extension portion 4032 which is columnar.
  • the first extending portion 4031 of the supporting portion 4003 is provided with a continuation portion 4311 connected to the second 4th connecting portion 4002 and a card connected to the continuation portion 4311 and the second extending portion 4032. Stop 4312.
  • the projection of the second extension portion 4032 in a direction away from the extending direction of the support portion 4003 falls within the locking portion 4312; the continuation portion 4311 along the support portion 4003 The projection in the extending direction also falls within the locking portion 4312.
  • the anti-drop member 4 may not penetrate the base 1, the shock absorbing member 3, and the mount 2.
  • the anti-drop member 4 has flexibility and is directly wound around the bottom arm 11 of the base 1 and the mounting arm 22 of the mount 2.
  • the anti-drop member 4 is in the form of a belt or a rope.
  • the anti-drop member 4 has flexibility, and can prevent the shock absorbing member 3 from falling off from the base 1 and/or the mounting seat 2 without affecting the function of the shock absorbing member 3. .
  • first receiving groove 13 and the second receiving groove may be omitted.
  • the first connecting portion 31 is directly connected to the surface of the base 1 adjacent to the mounting seat 2; the second connecting portion 32 is directly connected to the surface of the mounting base 2 adjacent to the base 1.
  • the above embodiment can also realize the connection of the damper member 3 to the base 1 and the mount 2.
  • the first abutting portion 41 is movably abutted from the outer surface of the base 1 away from the mounting seat 2.
  • the first abutting portion 41 may also be fixedly abutted from the outer surface of the base 1 away from the mounting seat 2; or the first abutting portion 41 and the base 1
  • the surface of the mount 2 is fixed to the junction.
  • the first contact portion 41 is integrally provided with the base 1.
  • the support portion 43 may have a certain elasticity as long as the first splicing portion 41, the second splicing portion 42, and the supporting portion 43 are The bonding force between the two is greater than the tensile force of the shock absorbing member 3.
  • the second connecting portion 42 and the outer surface of the mounting base 2 away from the base 1 are also movable.
  • the second contact portion 42 is fixedly abutted to the mounting seat 2.
  • the second abutting portion 42 can be fixedly abutted from the outer surface of the mounting arm 22 of the mounting seat 2 away from the base 1; or the second abutting portion 42 can be mounted with the mounting seat 2
  • the arm 22 is fixedly abutted near the outer surface of the base 1.
  • the support portion 43 has elasticity.
  • the shock absorbing effect achieved by the damper member 3 is assisted by the elasticity of the support portion 43; by the bonding force between the first abutting portion 41, the supporting portion 43 and the second abutting portion 42, The amount of movement of the damper member 3 is restricted to prevent the damper member 3 from coming off the base 1 and/or the mount 2.
  • the second junction 42 is disposed in the body of the mount.
  • the damper device 10 of the present invention can be used on the aircraft 100.
  • the aircraft 100 includes a body ⁇ , a stabilizing device 3 connected to the body ⁇ , and a camera 4 mounted on the stabilizing device 3.
  • the stabilizing device 3 can also be referred to as a pan/tilt.
  • the stabilization device 3 is mounted with the camera 4 to realize the aerial photography function of the aircraft 100.
  • the damper device 10 is connected to the body 1, and the stabilizing device 3, respectively.
  • the base 1 is connected to the body , and the stabilizing device 3 is connected to the mounting seat 2, and the damper portion 33 of the damper member 3 is stretched, so that the body 1 is generated.
  • the damper device 10 of the present invention has a shock absorbing function.
  • the aircraft 100 is equipped with the camera 4, which not only realizes the aerial photography function, but also achieves a good aerial photography effect, and can provide a stable aerial photography screen.
  • the fuselage 1 includes an arm and a rotor located on the arm and providing flight power to the aircraft 100.
  • the damper device 10 can also be located between the arm and the rotor.
  • the damper device 10 achieves multiple damper effects of the aircraft 100. Regardless of where the damper device 10 is located, it provides a good shock absorbing effect.
  • the damper device 10 of the present invention is applied to the aircraft 100 as a separate unit for easy disassembly and maintenance.
  • the fuselage, the damper 10 and the stabilizing device 3 may also be integrally formed.
  • a part or the whole of the damper device 10 may be integrally formed with the aircraft 100, for example, the base 1 and the body 1 of the aircraft 100 are integrally formed; the mounting seat 2 and the stabilizing device 3 , one-piece molding, etc.
  • the damper device 10 is not only used to connect components constituting the main body of the aircraft 100 (such as the center frame 11, the stabilizing device 3, the arm 12, or the rotor 14, It can also be used to connect other loads (such as cameras, GPS sensors, gyroscopes or other ancillary accessories) that the aircraft 100 is mounted on the fuselage.
  • a first distance L1 is defined between the base 1 and the mounting seat 2
  • a second distance L2 is disposed between the first 4-joint portion 4001 and the second abutting portion 4002.
  • the second distance L2 is greater than the first distance L1. The difference in distance between the second distance and the first distance is the stretched length of the shock absorbing member 3 when it is in operation.
  • the first abutting portion 4001 abuts the outer surface of the base 1 away from the mounting seat 2; the second abutting portion 4002 and the mounting The distance of the seat 2 away from the outer surface of the base 1 is gradually reduced.
  • the shock absorbing member 3 cannot continue to be stretched.
  • the bonding force between the first abutting portion 4001, the second abutting portion 4002, and the supporting portion 4003 is greater than the tensile force of the damper member 3.
  • the present invention prevents the shock absorbing member 3 from coming off the base 1 and/or the mount 2 by limiting the amount of movement of the shock absorbing member 3.
  • the anti-drop member 4 can also be installed between the bottom arm 12 of the base 1 and the mounting arm 22 of the mount 2 to prevent the shock absorbing member 3 from The falling between the base 1 and the mount 1 is not limited to the embodiment.
  • Embodiments of the present invention illustrate the beneficial effects of applying a damping device to an aircraft.
  • damper device of the present invention can apply to other products according to the disclosure of the specification.
  • the description is only a preferred embodiment of the present invention, and the scope of the present invention is not limited to the above-described embodiments, and equivalent modifications or variations made by those skilled in the art in light of the present disclosure should be included in the claims.

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

Abstract

一种减震装置（10）和应用所述减震装置（10）的飞行器（100）。所述减震装置（10）包括底座（1）和与所述底座（1）相隔一定距离的安装座（2）。所述减震装置（10）还包括至少一个夹设在所述底座（1）和所述安装座（2）之间的减震件（3）和分别连接所述底座（1）和所述安装座（2）的防脱落件（4），所述减震件（3）的一端与所述底座（1）相连，所述减震件（3）的另一端与所述安装座（2）相连，所述防脱落件（4）至少部分贯穿所述减震件（3）。减震装置（10）在所述底座（1）和所述安装座（2）间增设所述减震件（3），故具有减震功能。

Description

减震装置和应用所述减震装置的飞行器
【技术领域】
本发明属于飞行器技术领域，尤其涉及一种减震装置和应用所述减 震装置的飞行器。
【背景技术】
相关技术的飞行器其上通常携带负载实现某种特定功能， 例如， 所 述负载为相机或摄像机时， 其搭载在所述飞行器可实现航拍。 所述飞行 器包括机身和与所述机身相连的为飞行器提供飞行动力的动力装置。所 述负载与所述机身相连。
然而， 相关技术的所述飞行器， 所述负载和所述机身采用直接连接 这种硬连接方式。这样所述机身上的动力装置工作时产生的震动会直接 传递给所述负载， 导致所述负载跟随所述机身一起震动， 使所述飞行器 不能满足实际应用的需求。
因此， 实有必要提供一种减震装置。
【发明内容】
本发明的目的在于提供一种具有减震功能的减震装置。
本发明的目的是这样实现的： 一种减震装置， 其包括底座和与所述 底座相隔一定距离的安装座， 其中， 所述减震装置还包括至少一个夹设 在所述底座和所述安装座之间的减震件和分别连接所述底座和所述安 装座的防脱落件， 所述减震件的一端与所述底座相连， 所述减震件的另 一端与所述安装座相连， 所述防脱落件至少部分贯穿所述减震件。
优选地， 所述防脱落件包括用于与所述底座 4氏接的第一 4氏接部、 与 第一 4氏接部相隔一定距离的用于与所述安装座氏接的第二氏接部和连 接第一抵接部和第二抵接部的并贯穿所述减震件的支撑部。
优选地， 所述第二延伸部呈锥状。
优选地，所述第一 4氏接部与所述底座远离所述安装座的外表面活动 抵接。
优选地， 所述支撑部包括与所述第二抵接部相连的第一延伸部、 自 所述第一延伸部向远离所述第一抵接部延伸的第二延伸部和自所述第 二延伸部向远离所述第一延伸部延伸的所述第三延伸部； 所述第二延伸 部沿所述支撑部延伸方向的投影落在所述第三延伸部内； 所述第二延伸 部沿背离所述支撑部延伸方向的投影亦落在所述第一延伸部内。
优选地，所述支撑部的第一延伸部设有与第二抵接部相连的延续部 和分别连接所述延续部和所述第二延伸部的卡止部； 所述第二延伸部沿 背离所述支撑部延伸方向的投影落在所述卡止部内； 所述延续部沿所述 支撑部延伸方向的投影亦落在所述卡止部内。 7. 如权利要求 1所述的 减震装置， 其特征在于： 所述底座设有第一收容槽， 所述安装座设有第 二收容槽， 所述减震件包括收容在第一收容槽内的第一连接部、 收容在 第二收容槽内的第二连接部、连接所述第一连接部和所述第二连接部的 减震部。
优选地， 所述减震件由弹性材料制成。
优选地， 所述减震部设置为球形状。
本发明另提供一种减震装置，其包括底座和与所述底座相隔一定距 离的安装座， 其中， 所述减震装置还包括至少一个减震件和防脱落件， 所述减震件的一端与所述底座相连，所述减震件的另一端与所述安装座 相连， 所述防脱落件具有柔性且直接缠绕在所述底座和所述安装座上。
本发明另提供一种飞行器， 其包括如上所述的减震装置。
优选地， 所述飞行器包括机身和搭载于所述机身上的增稳装置， 所 述机身与所述减震装置的所述底座相连，所述增稳装置与所述减震装置 的所述安装座相连。
与相关技术相比较， 本发明的减震装置， 其在所述底座和所述安装 座间增设所述减震件， 故具有减震功能。 另外， 本发明另提供的应用所 述减震装置的飞行器，所述减震装置可抑制或消减所述飞行器产生的震 动。
【附图说明】
图 1为本发明的减震装置的立体图。
图 2为本发明的减震装置的立体分解图。
图 3为本发明的减震装置的减震部的立体图。
图 4为应用本发明的减震装置的防脱落件的第一种实施方式的立体 分解图。
图 5为应用本发明的减震装置的防脱落件的第二种实施方式的立体 分解图。
图 6为应用本发明的减震装置的防脱落件的第二种实施方式的立体 组装图。
图 7为应用本发明的减震装置的防脱落件的第三种实施方式的立体 分解图。
图 8为应用本发明的减震装置的飞行器立体图。
图 9为图 8中 A部分的放大图。
【具体实施方式】
如图 1至图 4所示，本发明实施例提供的一种减震装置 10为搭载其上 的负载（未图示）消减不必要的震动， 其包括底座 1、 与所述底座 1相隔一 定距离的安装座 2、 与所述底座 1和所述安装座 2均相连的至少一个减震 件 3。
所述底座 1包括一底板 11、 自所述底板 11散射延伸的若千底臂 12、 贯穿所述底臂 12的第一收容槽 13。 所述安装座 2包括安装板 21、 自所述安装板 21散射延伸的若千安装臂 22、 贯穿所述安装臂 22的第二收容槽 (未标号)。
本实施方式中，所述底臂 12和所述安装臂 22均设有四个且呈十字交 叉形。 故， 所述底臂 12、 所述第一收容槽 13、 所述安装臂 22和所述第二 收容槽的数量均为四个，与所述底臂 12和所述安装臂 22配合的所述减震 件 3亦设有四个。 任意所述减震件 3的一端与所述底座 1的所述底臂 12相 连， 相应地， 另一端与所述安装座 2的安装臂 22相连。
任意所述减震件 3呈中空状并夹设于所述底座 1和所述安装座 2之间， 其包括收容在所述底座 1的所述第一收容槽 13内的第一连接部 31、 收容 在所述安装座 2的所述第二收容槽内的第二连接部 32和连接所述第一连 接部 31和所述第二连接部 32的减震部 33。 为提供较好的减震效果， 所述 减震件 3由橡胶、 硅胶、 海绵或弹簧等弹性材料制成。 为了达到更好的 减震效果， 所述减震部 33设置为球形状。 工作时， 所述安装座 2以拉伸所述减震件 3的方式， 为搭接于所述安 装座 2上的所述负载消减所述底座 1产生的不必要的震动。所述第一连接 部 31和所述第二连接部 32分别活动地收容在所述第一收容槽 13和所述 第二收容槽内。 当所述安装座 2拉伸所述减震件 3时， 所述减震件 3容易 从所述安装座 2和 /或所述底座 1之间脱落。 为解决上述问题， 所述减震 装置 10还设有用以防止所述减震件 3从所述底座 1和 /或所述安装座 2脱 落的四个防脱落件 4。
请结合图 4所示， 所述防脱落件 4的第一种实施方式。 所述防脱落件 4包括用于与所述底座 14氏接的第一 4氏接部 41、与第一 4氏接部 41相隔一定 距离的用于与所述安装座 24氏接的第二 4氏接部 42、 连接所述第一 4氏接部 41和所述第二抵接部 42的并贯穿所述减震件 3的支撑部 43。 所述支撑部 43分别依次贯穿所述底座 1的所述第一收容槽 13、所述减震件 3的所述第 一连接部 31、 所述减震部 33、 所述减震件 3的所述第二连接部 32和所述 安装座 2的所述第二收容槽。 所述第一抵接部 41用于抵接于所述底座 1 远离所述安装座 2的外表面；所述第二抵接部 42用于抵接于所述安装座 2 远离所述底座 1的外表面。 本实施方式中， 所述防脱落件 4的支撑部 43 完全贯穿所述减震件 3。 在可选的实施方式中， 所述防脱落件 4可部分贯 穿减震件 3， 例如防脱落件 4仅贯穿减震部 33。
本实施方式中， 所述第二 4氏接部 42与所述支撑部 43—体设置。 所述 第一氏接部 41可通过螺紋或铆接等方式与所述支撑部 43固定相连，以方 便所述减震装置 10的组装和拆卸。 具体地， 所述第一抵接部 41包括用于 与所述底座 1抵接的所述第一抵接板 411、 自所述第一抵接板 411向所述 安装座 2延伸的固定部 412、 和同时贯穿所述第一 4氏接板 411和所述固定 部 412的固定孔 413， 所述支撑部 43插入于所述固定孔 413内。 本实施方 式中， 所述支撑部 43远离所述第二抵接部 42的一端设置有外螺紋 430， 所述固定孔 413内设置有内螺紋。所述支撑部 43通过外螺紋 430和所述固 定孔 413的内螺紋配合与所述第一氐接部 41相连接。 当然， 所述固定部 412可以省略， 所述固定孔 413直接与所述第一氏接板 411相连接。
在可选择的实施方式中， 所述第一氏接部 41、 所述第二氏接部 42 和所述支撑部 43分体设置， 组装时， 所述第一抵接部 41和所述第二抵接 部 42分别通过螺紋或铆接等本领域熟知的技术与所述支撑部 43固定相 连。
请参考图 5和图 6所示， 所述防脱落件 40的第二种实施方式。 所述第 二种实施方式的防脱落件 40与第一种实施方式的防脱落件 4大体类似， 不同的是：
所述支撑部 403包括与所述第二 4氏接部 402相连的第一延伸部 431、 自所述第一延伸部 431向远离所述第二抵接部 402延伸的第二延伸部 432 和自所述第二延伸部 432向远离所述第一延伸部 431延伸的所述第三延 伸部 433。 所述第二延伸部 432位于所述第一延伸部 431与所述第三延伸 部 433之间。 所述第二延伸部 432沿所述支撑部 403延伸方向的投影落在 所述第三延伸部 433内； 所述第二延伸部 432沿背离所述支撑部 403延伸 方向的投影落在所述第一延伸部 431内。从而使所述第一抵接部 401通过 固定孔 4013套设于所述第二延伸部 432上，并卡止于所述第一延伸部 431 和第三延伸部 433之间， 从而所述第一 4氏接部 401不易从所述支撑部 403 上脱落。 所述第二延伸部 432呈锥状， 自所述第一延伸部 431向第三延伸 部 433的方向， 所述第二延伸部 432的截面减缩。 为便于所述第一 4氏接部 401的组装， 所述第三延伸部 433亦呈锥状， 自所述第一延伸部 431向所 述第三延伸部 433的方向， 所述第三延伸部 433的截面减缩。
请参考图 7所示， 所述防脱落件 400的第三种实施方式。 所述第三种 实施方式的防脱落件 400与第二种实施方式的防脱落件 40大体类似， 不 同的是：
所述第一 4氏接部 4001套设于呈柱状的所述第二延伸部 4032上。所述 支撑部 4003的所述第一延伸部 4031设有与所述第二 4氏接部 4002相连的 延续部 4311和分部与所述延续部 4311和所述第二延伸部 4032相连的卡 止部 4312。 为减轻所述防脱落件 400的重量， 所述第二延伸部 4032沿背 离所述支撑部 4003延伸方向的投影落在所述卡止部 4312内；所述延续部 4311沿所述支撑部 4003延伸方向的投影亦落在所述卡止部 4312内。
在其他可选择的实施方式中，所述防脱落件 4可以不贯穿所述底座 1、 所述减震件 3和所述安装座 2。 具体地， 所述防脱落件 4具有柔性且直接 缠绕在所述底座 1的所述底臂 11和所述安装座 2的所述安装臂 22上。优选 地， 所述防脱落件 4呈带状或绳状。 所述防脱落件 4具有柔性， 在不影响 所述减震件 3功效的前提下， 亦可起到防止所述减震件 3从所述底座 1和 / 或所述安装座 2脱落的功效。
另外， 所述第一收容槽 13和所述第二收容槽可以省略。 所述第一连 接部 31直接与所述底座 1靠近所述安装座 2的表面相连；所述第二连接部 32直接与所述安装座 2靠近所述底座 1的表面相连。上述实施方式亦可实 现所述减震件 3与所述底座 1和所述安装座 2的连接。
为增强减震功效，所述第一抵接部 41与所述底座 1远离所述安装座 2 的外表面活动抵接。 在可选择的实施方式中， 所述第一抵接部 41亦可以 与所述底座 1远离所述安装座 2的外表面固定抵接；或者所述第一抵接部 41与所述底座 1靠近所述安装座 2的表面固定氏接。 在其他实施方式中， 所述第一氏接部 41与所述底座 1一体设置。
为增加所述减震件 3的拉伸量， 所述支撑部 43亦可以具有一定的弹 性， 只要所述第一氏接部 41、 所述第二氏接部 42和所述支撑部 43之间的 结合力大于所述减震件 3的拉伸力即可。
本实施方式中， 所述第二氏接部 42与所述安装座 2远离所述底座 1 的外表面亦为活动氏接。 在其他可选择的实施方式中， 所述第二氏接部 42与所述安装座 2固定抵接。所述第二抵接部 42可以与所述安装座 2的安 装臂 22上远离所述底座 1的外表面固定抵接； 或者第二抵接部 42可以与 所述安装座 2的所述安装臂 22上靠近所述底座 1的外表面固定抵接。此时， 所述支撑部 43具有弹性。 借助支撑部 43的弹性， 帮助所述减震件 3实现 的减震功效； 借助所述第一抵接部 41、 所述支撑部 43和所述第二抵接部 42之间的结合力， 限制所述减震件 3的移动量， 防止所述减震件 3从所述 底座 1和 /或所述安装座 2脱落。 在其他实施方式中， 所述第二 4氏接部 42 与所述安装座 2—体设置。
请进一步参阅图 8所示， 本发明的减震装置 10可用于飞行器 100 上。 具体地， 所述飞行器 100包括机身 Γ、 与所述机身 Γ相连的增稳装 置 3，和搭载在所述增稳装置 3，上的相机 4，。 所述增稳装置 3，亦可以称 之为云台。所述增稳装置 3，上搭载所述相机 4，实现所述飞行器 100的航 拍功能。 所述减震装置 10分别连接所述机身 1，和所述增稳装置 3，。 所述底座 1与机身 Γ相连， 所述增稳装置 3，与所述安装座 2相连， 通过拉伸所述减震件 3的所述减震部 33， 这样所述机身 1，产生的震动 可通过所述减震装置 10的所述减震件 3得到抑制或消减， 使得所述飞 行器 100产生的飞行动力稳定的传递给所述增稳装置 3，。 故， 本发明的 减震装置 10具有减震功能。 使得所述飞行器 100搭载相机 4，不仅实现 了航拍功能， 还实现了良好的航拍效果， 能够提供稳定的航拍画面。
另外， 所述机身 1，包括机臂和位于所述机臂上并为所述飞行器 100 提供飞行动力的旋翼。 所述减震装置 10亦可位于所述机臂和所述旋翼 之间。 这样所述减震装置 10则实现飞行器 100的多重减震效果。 无论 所述减震装置 10位于哪里， 都起到了良好的减震效果。
本发明的减震装置 10作为独立的单体应用于所述飞行器 100上， 便于拆卸和维修。 在可选择的实施方式中， 为方便所述飞行器 100的组 装， 所述机身 Γ、 所述减震装置 10和所述增稳装置 3，亦可以一体成型 设置。 或者， 所述减震装置 10的部分或整体可以与飞行器 100—体成 型， 比如所述底座 1与飞行器 100的所述机身 1，一体成型； 所述安装座 2与所述增稳装置 3，一体成型等。 另外， 所述减震装置 10不仅用于连 接组成所述飞行器 100的主体的组件 (如所述中心架 11，、 所述增稳装置 3，、 所述机臂 12，或所述旋翼 14，）， 其也可用于连接所述飞行器 100搭 载在所述机身上的其他负载 (如相机、 GPS 传感器、 陀螺仪或其他辅助 配件）。
请结合图 1至图 9所示，当所述减震件 3未被拉伸时，受重力的作用， 所述第一抵接部 41抵接于所述底座 1远离所述安装座 2的外表面；所述第 二 4氏接部 42与所述安装座 2的外表面相隔一定的距离。 这样， 所述底座 1 和所述安装座 2之间设有第一距离 L 1， 所述第一 4氏接部 4001和所述第二 抵接部 4002之间设有第二距离 L2。 所述第二距离 L2大于所述第一距离 Ll。 所述第二距离和第一距离之间的距离差， 为所述减震件 3工作时的 拉伸长度。
当所述减震件 3逐渐被拉伸时， 所述第一抵接部 4001抵接于所述底 座 1远离所述安装座 2的外表面； 所述第二抵接部 4002与所述安装座 2远 离所述底座 1的外表面的距离逐渐缩小。 当第二抵接部 4002抵接于所述 安装座 2远离所述底座 1的外表面时，所述减震件 3不能继续拉伸。此时， 所述第一抵接部 4001、所述第二抵接部 4002和所述支撑部 4003之间的结 合力大于所述减震件 3的拉伸力。本发明通过限制所述减震件 3的移动量， 防止所述减震件 3从所述底座 1和 /或所述安装座 2脱落。
可以理解的是， 实际应用中， 所述防脱落件 4也可安装于所述底座 1 的底臂 12和所述安装座 2的安装臂 22之间，用以防止所述减震件 3从所述 底座 1和安装座 1之间脱落， 并不限于本实施方式。
本发明的实施方式以减震装置应用于飞行器上阐述有益效果。当然， 本领域技术人员根据说明书公开的内容，还可以将本发明的减震装置应 用于其他产品上。 说明书仅为本发明的较佳实施方式， 本发明的保护范 围并不以上述实施方式为限，但凡本领域普通技术人员根据本发明所揭 示内容所作的等效修饰或变化，皆应纳入权利要求书中记载的保护范围 内。

Claims

权利要求书
1. 一种减震装置， 其包括底座和与所述底座相隔一定距离的安装 座， 其特征在于： 所述减震装置还包括至少一个夹设在所述底座和所述 安装座之间的减震件和分别连接所述底座和所述安装座的防脱落件，所 述减震件的一端与所述底座相连，所述减震件的另一端与所述安装座相 连， 所述防脱落件安装于所述底座和所述安装座之间， 用以防止所述减 震件从所述底座和所述安装座之间脱落。
2. 如权利要求 1所述的减震装置， 其特征在于： 所述防脱落件包 括用于与所述底座氏接的第一 4氏接部、与第一氏接部相隔一定距离的用 于与所述安装座抵接的第二抵接部和连接第一抵接部和第二抵接部的 并贯穿所述减震件的支撑部，所述第一抵接部与所述底座远离所述安装 座的外表面活动抵接，所述第二抵接部与所述安装座远离所述底座的外 表面亦为活动氏接。
3. 如权利要求 1所述的减震装置， 其特征在于： 所述防脱落件包 括用于与所述底座氏接的第一 4氏接部、与第一氏接部相隔一定距离的用 于与所述安装座抵接的第二抵接部和连接第一抵接部和第二抵接部的 并贯穿所述减震件的支撑部， 所述第一抵接部与所述底座一体设置。
4.如权利要求 3所述的减震装置， 其特征在于： 所述第二抵接部与 所述安装座一体设置， 所述支撑部具有弹性。
5. 如权利要求 2所述的减震装置， 其特征在于： 所述第二延伸部 呈锥状。
6. 如权利要求 2所述的减震装置， 其特征在于： 所述支撑部包括 与所述第二抵接部相连的第一延伸部、 自所述第一延伸部向远离所述第 一 4氏接部延伸的第二延伸部和自所述第二延伸部向远离所述第一延伸 部延伸的所述第三延伸部； 所述第二延伸部沿所述支撑部延伸方向的投 影落在所述第三延伸部内； 所述第二延伸部沿背离所述支撑部延伸方向 的投影亦落在所述第一延伸部内。
7. 如权利要求 1所述的减震装置， 其特征在于： 所述底座设有第 一收容槽， 所述安装座设有第二收容槽， 所述减震件包括收容在第一收 容槽内的第一连接部、 收容在第二收容槽内的第二连接部、 连接所述第 一连接部和所述第二连接部的减震部。
8. 如权利要求 7所述的减震装置， 其特征在于： 所述减震部设置 为球形状。
9. 一种飞行器， 其特征在于： 所述飞行器包括如权利要求 1 至 8 任意一项所述的减震装置。
10. 如权利要求 9所述的飞行器， 其特征在于： 所述飞行器包括机 身和搭载于所述机身上的增稳装置，所述机身与所述减震装置的所述底 座相连， 所述增稳装置与所述减震装置的所述安装座相连。
2
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JP2017013767A (ja) * 2015-07-07 2017-01-19 株式会社マルチコプターラボ マルチコプター
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EP3505452A4 (en) * 2016-11-09 2020-05-13 Sekisui Polymatech Co., Ltd. VIBRATION CONTROL DEVICE AND UNMANNED AIRCRAFT
EP3546376A4 (en) * 2016-11-23 2020-07-22 Yau, Chi Pang CAMERA MOUNTING DEVICE USED IN OBLIQUE PHOTOGRAPHY PHOTOGRAPHED FROM AN UNPILOT AIR VEHICLE
CN106742009A (zh) * 2017-03-14 2017-05-31 中交遥感载荷（北京）科技有限公司 带有防抖式可调节相机挂架的无人机起落支撑架总成
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