WO2018027686A1 - Mécanisme de tampon pour aéronef sans pilote - Google Patents

Mécanisme de tampon pour aéronef sans pilote Download PDF

Info

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)
Chinese (zh)
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/fr
Publication of WO2018027686A1 publication Critical patent/WO2018027686A1/fr

Links

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 Prevention Devices (AREA)
  • Vibration Dampers (AREA)

Abstract

L'invention concerne un mécanisme de tampon pour un aéronef sans pilote, comprenant deux montants (1) et un panneau (2) permettant de monter l'aéronef sans pilote, le panneau (2) étant disposé sur celui-ci avec des supports (20) permettant de maintenir les montants (1); une cavité creuse (21) est ménagée à l'intérieur du panneau (2), et la cavité creuse (21) est pourvue en son sein d'une carte tampon (210) et de deux tampons d'amortissement (211) prenant en sandwich la carte tampon entre eux; une extrémité de chacun des supports (20) est fixée sur la carte tampon (210); le panneau (2) est pourvu, sur celui-ci, de trous traversants (22) s'ajustant avec les supports (20). Lorsque l'aéronef sans pilote décolle et atterrit, le choc reçu par les montants (1) est transféré à la carte tampon (210) par l'intermédiaire des supports (20), et le choc est absorbé au moyen des tampons d'amortissement (211) sur les surfaces supérieure et inférieure de la carte tampon (210), empêchant efficacement un effet de choc, de telle sorte que la carrosserie de véhicule est protégée. Le mécanisme de tampon a une structure globale simple et est peu coûteux.
PCT/CN2016/094429 2016-08-10 2016-08-10 Mécanisme de tampon pour aéronef sans pilote WO2018027686A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/094429 WO2018027686A1 (fr) 2016-08-10 2016-08-10 Mécanisme de tampon pour aéronef sans pilote

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/094429 WO2018027686A1 (fr) 2016-08-10 2016-08-10 Mécanisme de tampon pour aéronef sans pilote

Publications (1)

Publication Number Publication Date
WO2018027686A1 true WO2018027686A1 (fr) 2018-02-15

Family

ID=61161517

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/094429 WO2018027686A1 (fr) 2016-08-10 2016-08-10 Mécanisme de tampon pour aéronef sans pilote

Country Status (1)

Country Link
WO (1) WO2018027686A1 (fr)

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
Publication number Priority date Publication date Assignee Title
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 (fr) * 2014-05-13 2015-11-18 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Système de liaison à amortissement pour un train d'atterrissage giravion
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 (fr) * 2014-05-13 2015-11-18 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Système de liaison à amortissement pour un train d'atterrissage giravion
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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