WO2021168748A1 - 一种快递无人机 - Google Patents

一种快递无人机 Download PDF

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Publication number
WO2021168748A1
WO2021168748A1 PCT/CN2020/077014 CN2020077014W WO2021168748A1 WO 2021168748 A1 WO2021168748 A1 WO 2021168748A1 CN 2020077014 W CN2020077014 W CN 2020077014W WO 2021168748 A1 WO2021168748 A1 WO 2021168748A1
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WO
WIPO (PCT)
Prior art keywords
mounting plate
fuselage
mounting
counterweight
express
Prior art date
Application number
PCT/CN2020/077014
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English (en)
French (fr)
Inventor
杨哲
Original Assignee
南京唐壹信息科技有限公司
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 南京唐壹信息科技有限公司 filed Critical 南京唐壹信息科技有限公司
Priority to PCT/CN2020/077014 priority Critical patent/WO2021168748A1/zh
Publication of WO2021168748A1 publication Critical patent/WO2021168748A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U60/00—Undercarriages
    • B64U60/50—Undercarriages with landing legs
    • 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
    • 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

Definitions

  • the invention relates to an express drone.
  • the present invention provides an express drone in order to solve the above-mentioned problems in the prior art.
  • An express drone includes a fuselage, a rotor assembly arranged on the fuselage, and an electric control assembly for remotely controlling the rotor assembly, and also includes a buffer column and a holder.
  • the four buffer columns are all vertically fixedly connected to the aircraft.
  • the holder is fixedly connected to the upper end surface of the body;
  • the buffer column includes a mounting column, a spring, a buffer sleeve and a mounting cap.
  • the mounting column is vertically fixed on the fuselage.
  • a positioning step is provided on the mounting column.
  • the buffer sleeve and the mounting cap are both sleeved on the mounting column.
  • the installation cap and the buffer sleeve are respectively located on the upper and lower sides of the positioning step, the installation cap is threadedly connected with the buffer sleeve, the spring is sleeved on the installation column, and the upper end of the spring abuts on the positioning step, and the lower end abuts inside the buffer sleeve. Cavity.
  • the holder includes an upper mounting plate, a lower mounting plate, a fixing column and a counterweight.
  • the upper mounting plate and the lower mounting plate are arranged in parallel with each other, and a storage cavity is formed between the upper mounting plate and the lower mounting plate.
  • a number of fixed columns are fixed between the upper mounting plate and the lower mounting plate.
  • the fixed columns are perpendicular to the upper and lower mounting plates.
  • the counterweight is detachably plugged into one or more fixed columns, and the lower mounting plate is fixedly connected to the machine. Body.
  • the counterweight includes a metal block and a rubber block, the rubber block is arranged inside the metal block, and an insertion slot is provided on the counterweight block, and the insertion slot penetrates the metal block and the rubber block.
  • the metal block and the rubber block are both circular structures, and the insertion groove is arranged along the radial direction of the counterweight.
  • the invention is provided with a buffer to ensure the buffer when the drone is landed when the drone is transported with a load, and reduce the vibration damage of the drone.
  • Figure 1 is a structural diagram of the present invention.
  • Figure 2 is a structural diagram of a buffer column in the present invention.
  • Figure 3 is a structural diagram of the counterweight in the present invention.
  • an express drone of the present invention includes a fuselage 1, a buffer column 3, a storage seat 5, a rotor assembly 2 arranged on the fuselage 1, and an electric control assembly for remotely controlling the rotor assembly .
  • the four buffer columns 3 are all vertically fixedly connected to the bottom surface of the fuselage 1, and the holder 5 is fixedly connected to the upper end surface of the fuselage 1.
  • the buffer column 3 includes a mounting column 31, a spring 32, a buffer sleeve 33, and a mounting cap 34.
  • the mounting column 31 is vertically fixed on the fuselage 1, and a positioning step 35 is provided on the mounting column 31.
  • the buffer sleeve 33 and the mounting cap 34 are both It is sleeved on the installation post 31, and the installation cap 34 and the buffer sleeve 33 are respectively located on the upper and lower sides of the positioning step 35.
  • the mounting cap 34 and the buffer sleeve 33 are threadedly connected, the spring 32 is sleeved on the mounting post 31, and the spring 32 is placed in the buffer sleeve 33, the upper end of the spring 32 abuts on the positioning step 35, and the lower end of the spring 32 abuts on the The inner cavity of the buffer sleeve 33.
  • the buffer sleeve 33 acts on the bottom surface, and the spring 32 is compressed to play a buffering role.
  • the holder 5 in the present invention includes an upper mounting plate 51, a lower mounting plate 52, a fixing column 53 and a counterweight 54.
  • the upper mounting plate 51 and the lower mounting plate 52 are arranged parallel to each other, and the upper mounting plate 51 and the lower mounting plate 52
  • a storage cavity is formed between the upper mounting plate 51 and the lower mounting plate 52.
  • a number of fixing posts 53 are fixed between the upper mounting plate 51 and the lower mounting plate 52.
  • the fixing posts 53 are perpendicular to the upper and lower mounting plates.
  • the upper and lower mounting plates 52 of the fixing column 53 are fixedly connected to the fuselage 1.
  • the counterweight 54 includes a metal block 541 and a rubber block 542.
  • the rubber block 542 is provided on the inner side of the metal block 541.
  • the counterweight 54 is provided with an insertion slot 543 which penetrates the metal block 541 and the rubber block 542. .
  • Both the metal block 541 and the rubber block 54 have a circular structure, and the insertion groove 543 is arranged along the radial direction of the counterweight 54.
  • the rubber block When the counterweight is in use, the rubber block is elastically hugged on the fixed post 53 by the rubber block itself, that is, the rubber block and the fixed post 53 are in an interference fit.
  • the invention can facilitate the transportation of materials, and can be used for medical rescue, express delivery, fire rescue and other purposes.
  • the balance of the drone is ensured by adding or reducing counterweights.
  • the counterweight has a simple structure and is easy to install.
  • the self-elasticity of the rubber ensures the fixation and the use effect is good.

Landscapes

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

Abstract

一种快递无人机，包括机身（1），设于机身（1）上的旋翼组件（2）以及对旋翼组件（2）进行远程控制的电控制组件，还包括缓冲柱（3）和置物座（5），四根缓冲柱（3）均竖直固定连接在机身（1）的底面上，置物座（5）固定连接在机身（1）的上端面上。在无人机载重运输落地时，保证落地时缓冲，减少无人机震动损坏。

Description

一种快递无人机 技术领域：
本发明涉及一种快递无人机。
背景技术：
现有的无人机在落地时由于受到惯性的作用会产生强烈的震动，长时间如此会造成无人机零件受损变形或零件松动脱落。因此，确有必要对现有技术进行改进以解决现有技术之不足。
发明内容：
本发明是为了解决上述现有技术存在的问题而提供一种快递无人机。
本发明所采用的技术方案有：
一种快递无人机，包括机身、设于机身上的旋翼组件以及对旋翼组件进行远程控制的电控制组件，还包括缓冲柱和置物座，四根缓冲柱均竖直固定连接在机身的底面上，置物座固定连接在机身的上端面上；
所述缓冲柱包括安装柱、弹簧、缓冲套和安装帽，所述安装柱竖直固定在机身上，在安装柱上设有定位台阶，缓冲套和安装帽均套设在安装柱上，且安装帽和缓冲套分别位于定位台阶的上下两侧，所述安装帽与缓冲套螺纹连接，弹簧套设在安装柱上，且弹簧的上端抵触在定位台阶上，下端抵触在缓冲套的内腔上。
进一步地，所述置物座包括上安装板、下安装板、固定柱和配重块，所述上安装板与下安装板相互平行设置，上安装板与下安装板之间形成置物腔，在上安装板与下安装板之间固定若干根固定柱，固定柱垂直于上、下安装板，配重块可拆卸地插接于一根或多根固定柱上，下安装板固定连接在机身上。
进一步地，所述配重块包括金属块和橡胶块，所述橡胶块设于金属块的内侧，在配重块上设有插接槽，所述插接槽贯穿于金属块和橡胶块。
进一步地，所述金属块和橡胶块均为圆形结构，插接槽沿着配重块的径向方向设置。
本发明具有如下有益效果：
本发明设置缓冲，在无人机载重运输落地时，保证落地时缓冲，减少无人机震动损坏。
附图说明：
图1为本发明结构图。
图2为本发明中缓冲柱的结构图。
图3为本发明中配重块的结构图。
具体实施方式：
下面结合附图对本发明作进一步的说明。
如图1至图3，本发明一种快递无人机，包括机身1、缓冲柱3、置物座5、设于机身1上的旋翼组件2以及对旋翼组件进行远程控制的电控制组件。四根缓冲柱3均竖直固定连接在机身1的底面上，置物座5固定连接在机身1的上端面上。
缓冲柱3包括安装柱31、弹簧32、缓冲套33和安装帽34，安装柱31竖直固定在机身1上，在安装柱31上设有定位台阶35，缓冲套33和安装帽34均套设在安装柱31上，且安装帽34和缓冲套33分别位于定位台阶35的上下两侧。安装帽34与缓冲套33之间螺纹连接，弹簧32套设在安装柱31上，且弹簧32置于缓冲套33的内存，弹簧32的上端抵触在定位台阶35上，弹簧32的下端抵触在缓冲套33的内腔上。
在无人机下落时，缓冲套33作用于底面上，弹簧32被压缩，起到缓冲的作用。
本发明中的置物座5包括上安装板51、下安装板52、固定柱53和配重块54，上安装板51与下安装板52相互平行设置，上安装板51与下安装板52之间形成置物腔，在上安装板51与下安装板52之间固定若干根固定柱53，固定柱53垂直于上、下安装板，配重块54可拆卸地插接于一根或多根固定柱53上，下安装板52固定连接在机身1上。
配重块54包括金属块541和橡胶块542，橡胶块542设于金属块541的内侧，在配重块54上设有插接槽543，插接槽543贯穿于金属块541和橡胶块542。
金属块541和橡胶块54均为圆形结构，插接槽543沿着配重块54的径向方向设置。
配重块在使用时，通过橡胶块自身弹性抱紧在固定柱53上，即橡胶块与固定柱53之间过盈配合。
本发明可以便于运输物资，可以作为医用救援、快递、消防救援等用途，在运输物品时，通过增减配重块保证无人机的平衡，配重块结构简单，配重块方便安装，通过橡胶的自身弹性保证固定，使用效果好。
以上所述仅是本发明的优选实施方式，应当指出，对于本技术领域的普通技术人员 来说，在不脱离本发明原理的前提下还可以作出若干改进，这些改进也应视为本发明的保护范围。

Claims (4)

  1. 一种快递无人机，包括机身(1)、设于机身(1)上的旋翼组件(2)以及对旋翼组件进行远程控制的电控制组件，其特征在于：还包括缓冲柱(3)和置物座(5)，四根缓冲柱(3)均竖直固定连接在机身(1)的底面上，置物座(5)固定连接在机身(1)的上端面上；
    所述缓冲柱(3)包括安装柱(31)、弹簧(32)、缓冲套(33)和安装帽(34)，所述安装柱(31)竖直固定在机身(1)上，在安装柱(31)上设有定位台阶(35)，缓冲套(33)和安装帽(34)均套设在安装柱(31)上，且安装帽(34)和缓冲套(33)分别位于定位台阶(35)的上下两侧，所述安装帽(34)与缓冲套(33)螺纹连接，弹簧(32)套设在安装柱(31)上，且弹簧(32)的上端抵触在定位台阶(35)上，下端抵触在缓冲套(33)的内腔上。
  2. 如权利要求1所述的快递无人机，其特征在于：所述置物座(5)包括上安装板(51)、下安装板(52)、固定柱(53)和配重块(54)，所述上安装板(51)与下安装板(52)相互平行设置，上安装板(51)与下安装板(52)之间形成置物腔，在上安装板(51)与下安装板(52)之间固定若干根固定柱(53)，固定柱(53)垂直于上、下安装板，配重块(54)可拆卸地插接于一根或多根固定柱(53)上，下安装板(52)固定连接在机身(1)上。
  3. 如权利要求2所述的快递无人机，其特征在于：所述配重块(54)包括金属块(541)和橡胶块(542)，所述橡胶块(542)设于金属块(541)的内侧，在配重块(54)上设有插接槽(543)，所述插接槽(543)贯穿于金属块(541)和橡胶块(542)。
  4. 如权利要求3所述的快递无人机，其特征在于：所述金属块(541)和橡胶块(542)均为圆形结构，插接槽(543)沿着配重块(54)的径向方向设置。
PCT/CN2020/077014 2020-02-27 2020-02-27 一种快递无人机 WO2021168748A1 (zh)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010140082A1 (en) * 2009-06-04 2010-12-09 Cape Peninsula University Of Technology Unmanned aerial vehicle
US20180099741A1 (en) * 2016-10-12 2018-04-12 Intel Corporation Multi-stage reduction of impact forces
CN109693787A (zh) * 2019-01-29 2019-04-30 深圳市律远汇智科技有限公司 一种具有水平调节功能的可靠性高的物流无人机
CN208842622U (zh) * 2018-09-29 2019-05-10 南通志乐新材料有限公司 一种雨天防水速递无人机
CN209889097U (zh) * 2019-04-26 2020-01-03 山东省地质矿产勘查开发局第四地质大队(山东省第四地质矿产勘查院) 一种旋翼无人机起落架及旋翼无人机

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010140082A1 (en) * 2009-06-04 2010-12-09 Cape Peninsula University Of Technology Unmanned aerial vehicle
US20180099741A1 (en) * 2016-10-12 2018-04-12 Intel Corporation Multi-stage reduction of impact forces
CN208842622U (zh) * 2018-09-29 2019-05-10 南通志乐新材料有限公司 一种雨天防水速递无人机
CN109693787A (zh) * 2019-01-29 2019-04-30 深圳市律远汇智科技有限公司 一种具有水平调节功能的可靠性高的物流无人机
CN209889097U (zh) * 2019-04-26 2020-01-03 山东省地质矿产勘查开发局第四地质大队(山东省第四地质矿产勘查院) 一种旋翼无人机起落架及旋翼无人机

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