WO2018027686A1 - 一种无人机缓冲机构 - Google Patents

一种无人机缓冲机构 Download PDF

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Publication number
WO2018027686A1
WO2018027686A1 PCT/CN2016/094429 CN2016094429W WO2018027686A1 WO 2018027686 A1 WO2018027686 A1 WO 2018027686A1 CN 2016094429 W CN2016094429 W CN 2016094429W WO 2018027686 A1 WO2018027686 A1 WO 2018027686A1
Authority
WO
WIPO (PCT)
Prior art keywords
buffer
panel
unmanned aerial
aerial vehicle
hollow cavity
Prior art date
Application number
PCT/CN2016/094429
Other languages
English (en)
French (fr)
Inventor
张琬彬
Original Assignee
张琬彬
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 张琬彬 filed Critical 张琬彬
Priority to PCT/CN2016/094429 priority Critical patent/WO2018027686A1/zh
Publication of WO2018027686A1 publication Critical patent/WO2018027686A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B64C25/62—Spring shock-absorbers; Springs

Definitions

  • the present invention relates to the field of drone technology, and more particularly to a drone buffer mechanism.
  • UAVs are unmanned aircraft operated by radio remote control equipment and self-provided program control devices. Civil drones have important applications in aerial photography, agriculture, plant protection, disaster relief, etc.; drones need to take off and land.
  • the shock absorber is used to protect the fuselage. The structure of the shock absorbing cushion mechanism currently used is complicated or unreasonable, and the shock absorbing effect is not satisfactory.
  • the technical problem to be solved by the present invention is to provide a UAV buffer mechanism with good shock absorption and buffering effect against the above-mentioned drawbacks of the prior art.
  • a drone buffer mechanism comprising two tripods and a panel for installing the drone; wherein the panel is provided with a clamping member for clamping the tripod; the panel is internally provided with a hollow a cavity, the buffer cavity is internally provided with a buffer plate and two cushions for clamping the buffer plate; the end of the clamp is fixedly disposed with the buffer plate; and the panel is provided with The through hole of the clamping member.
  • the buffer plate and the hollow cavity side wall are connected by a metal elastic rope.
  • the four corners of the lower surface of the baffle plate are connected to the hollow cavity through a spring.
  • the cushioning surface and the hollow cavity contact surface are provided with wave-shaped protrusions.
  • the utility model has the beneficial effects that when the drone is taken off and landed, the vibration of the tripod is transmitted to the buffer plate through the clamping member, and the vibration is absorbed by the two cushions on the lower surface of the buffer plate, thereby effectively preventing the vibration.
  • the effect is to protect the fuselage; the overall structure is simple and the cost is low.
  • FIG. 1 is a schematic view showing the structure of a buffer mechanism of a drone according to a preferred embodiment of the present invention.
  • the unmanned aerial vehicle buffer mechanism of the preferred embodiment of the present invention includes a UAV buffer mechanism, including two tripods 1 and a panel 2 for installing the drone, and the panel 2 is provided with a clip.
  • the portion is fixedly disposed with the buffer plate 210;
  • the panel 2 is provided with a through hole 22 that cooperates with the clamping member 20; when the drone is taken off and landed, the vibration received by the stand 1 is transmitted to the buffer plate 210 through the clamping member 20,
  • the vibration is absorbed by the two cushions 211 on the upper and lower surfaces of the buffer plate 210, thereby effectively preventing the vibration, thereby protecting the body; the overall structure is simple and the cost is low.
  • the buffer plate 210 and the side wall of the hollow cavity 21 are connected by a metal elastic cord 212 to prevent displacement of the buffer plate 210, thereby ensuring the stability of the stand 1 and facilitating the transmission and absorption of vibration.
  • the four corners of the upper and lower surfaces of the buffer plate 210 are connected to the hollow cavity 21 through the spring 23, and the shock absorption effect is good and the balance is high.
  • the contact surface of the cushion 211 and the hollow cavity 21 is provided with a wave-shaped protrusion 213 to prolong the buffering time and improve the cushioning and damping effect.

Landscapes

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

Abstract

一种无人机缓冲机构，包括两个脚架（1）和用于安装无人机的面板（2），面板（2）上设置有夹持脚架（1）的夹持件（20）；面板（2）内部设置有镂空型腔（21），镂空型腔（21）内部设置有缓冲板（210）和上下包夹缓冲板的两块减震垫（211）；夹持件（20）端部与缓冲板（210）固定设置；面板上（2）设置有与夹持件（20）配合的通孔（22）；无人机在起飞和降落时，脚架（1）承受的震动通过夹持件（20）传导至缓冲板（210），通过缓冲板（1）上下表面的两块减震垫（211）对震动进行吸收，有效防止了震动影响，从而保护了机身；整体结构简单，成本低。

Description

一种无人机缓冲机构 技术领域
本发明涉及无人机技术领域，更具体地说，涉及一种无人机缓冲机构。
 背景技术
无人机是利用无线电遥控设备和自备的程序控制装置操纵的不载人飞机，民用无人机在航拍、农业、植保、救灾等领域有着较重要应用；无人机在起飞和降落时需要进行减震以保护机身，目前使用的减震缓冲机构结构较复杂或设置不合理，减震效果不理想。
 技术问题
本发明要解决的技术问题在于，针对现有技术的上述缺陷，提供一种减震缓冲效果好的无人机缓冲机构。
 技术解决方案
本发明解决其技术问题所采用的技术方案是：
构造一种无人机缓冲机构，包括两个脚架和用于安装无人机的面板；其中，所述面板上设置有夹持所述脚架的夹持件；所述面板内部设置有镂空型腔，所述镂空型腔内部设置有缓冲板和上下包夹所述缓冲板的两块减震垫；所述夹持件端部与所述缓冲板固定设置；所述面板上设置有与所述夹持件配合的通孔。
本发明所述的无人机缓冲机构，其中，所述缓冲板与所述镂空型腔侧壁通过金属弹性绳连接。
本发明所述的无人机缓冲机构，其中，所述缓冲板上下表面四个边角处均与所述镂空型腔通过弹簧连接。
本发明所述的无人机缓冲机构，其中，所述减震垫与所述镂空型腔接触表面设置有波浪型凸起。
 有益效果
本发明的有益效果在于：无人机在起飞和降落时，脚架承受的震动通过夹持件传导至缓冲板，通过缓冲板上下表面的两块减震垫对震动进行吸收，有效防止了震动影响，从而保护了机身；整体结构简单，成本低。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将结合附图及实施例对本发明作进一步说明，下面描述中的附图仅仅是本发明的部分实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他附图：
图1是本发明较佳实施例的无人机缓冲机构结构示意图。
 本发明的实施方式
为了使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的技术方案进行清楚、完整的描述，显然，所描述的实施例是本发明的部分实施例，而不是全部实施例。基于本发明的实施例，本领域普通技术人员在没有付出创造性劳动的前提下所获得的所有其他实施例，都属于本发明的保护范围。
本发明较佳实施例的无人机缓冲机构如图1所示，包括一种无人机缓冲机构，包括两个脚架1和用于安装无人机的面板2，面板2上设置有夹持脚架1的夹持件20；面板2内部设置有镂空型腔21，镂空型腔21内部设置有缓冲板210和上下包夹缓冲板210的两块减震垫211；夹持件20端部与缓冲板210固定设置；面板2上设置有与夹持件20配合的通孔22；无人机在起飞和降落时，脚架1承受的震动通过夹持件20传导至缓冲板210，通过缓冲板210上下表面的两块减震垫211对震动进行吸收，有效防止了震动影响，从而保护了机身；整体结构简单，成本低。
如图1所示，缓冲板210与镂空型腔21侧壁通过金属弹性绳212连接，防止缓冲板210发生位移，保证脚架1稳定性的同时便于震动的传导和吸收。
如图1所示，缓冲板210上下表面四个边角处均与镂空型腔21通过弹簧23连接，减震效果好且平衡性高。
如图1所示，减震垫211与镂空型腔21接触表面设置有波浪型凸起213，延长缓冲时间，提高缓冲减震效果。
应当理解的是，对本领域普通技术人员来说，可以根据上述说明加以改进或变换，而所有这些改进和变换都应属于本发明所附权利要求的保护范围。

Claims (4)

  1. 一种无人机缓冲机构，包括两个脚架和用于安装无人机的面板；其特征在于，所述面板上设置有夹持所述脚架的夹持件；所述面板内部设置有镂空型腔，所述镂空型腔内部设置有缓冲板和上下包夹所述缓冲板的两块减震垫；所述夹持件端部与所述缓冲板固定设置；所述面板上设置有与所述夹持件配合的通孔。
  2. 根据权利要求1所述的无人机缓冲机构，其特征在于，所述缓冲板与所述镂空型腔侧壁通过金属弹性绳连接。
  3. 根据权利要求1所述的无人机缓冲机构，其特征在于，所述缓冲板上下表面四个边角处均与所述镂空型腔通过弹簧连接。
  4. 根据权利要求1所述的无人机缓冲机构，其特征在于，所述减震垫与所述镂空型腔接触表面设置有波浪型凸起。
PCT/CN2016/094429 2016-08-10 2016-08-10 一种无人机缓冲机构 WO2018027686A1 (zh)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114422433A (zh) * 2021-12-29 2022-04-29 江苏德联达智能科技有限公司 防摔减震路由器

Citations (7)

* Cited by examiner, † Cited by third party
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US20030057321A1 (en) * 2001-09-24 2003-03-27 Temple Larry Dan Landing gear for model airplane
CN204527660U (zh) * 2015-02-13 2015-08-05 湖北大秀天域科技发展有限公司 多旋翼无人机
CN104859838A (zh) * 2015-06-03 2015-08-26 中恒天信（天津）航空科技有限公司 一种油动多旋翼无人飞行平台
CN104908963A (zh) * 2015-06-24 2015-09-16 广州飞米电子科技有限公司 减震结构、具有减震功能的惯性测量结构和飞行器
EP2944567A1 (en) * 2014-05-13 2015-11-18 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Linking damper system for a rotorcraft landing gear
CN205239940U (zh) * 2015-11-18 2016-05-18 广州广鸿航空科技有限公司 一种无人机发动机减震机构
CN106275395A (zh) * 2016-08-10 2017-01-04 张琬彬 一种无人机缓冲机构

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030057321A1 (en) * 2001-09-24 2003-03-27 Temple Larry Dan Landing gear for model airplane
EP2944567A1 (en) * 2014-05-13 2015-11-18 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Linking damper system for a rotorcraft landing gear
CN204527660U (zh) * 2015-02-13 2015-08-05 湖北大秀天域科技发展有限公司 多旋翼无人机
CN104859838A (zh) * 2015-06-03 2015-08-26 中恒天信（天津）航空科技有限公司 一种油动多旋翼无人飞行平台
CN104908963A (zh) * 2015-06-24 2015-09-16 广州飞米电子科技有限公司 减震结构、具有减震功能的惯性测量结构和飞行器
CN205239940U (zh) * 2015-11-18 2016-05-18 广州广鸿航空科技有限公司 一种无人机发动机减震机构
CN106275395A (zh) * 2016-08-10 2017-01-04 张琬彬 一种无人机缓冲机构

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114422433A (zh) * 2021-12-29 2022-04-29 江苏德联达智能科技有限公司 防摔减震路由器

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